Wing for an aircraft, incorporating a de-icing system
The movable wingtip with an integrated de-icing system addresses the challenge of de-icing the upper surface of raised wingtips by using a conduit and hot air distribution, ensuring effective de-icing across positions.
Patent Information
- Application Number
- FR2024006720
- Authority / Receiving Office
- FR · FR
- Patent Type
- Applications
- Current Assignee / Owner
- Filing Date
- 2024-06-21
- Publication Date
- 2025-12-26
AI Technical Summary
Existing aircraft wings with folding wingtips face challenges in de-icing the upper surface of the wingtip when raised, as de-icing fluids struggle to reach and maintain contact due to vertical orientation, leading to delayed and reduced de-icing effectiveness.
Aircraft wing design incorporating a movable wingtip with an integrated de-icing system featuring a conduit and supply duct connected to a hot air source, allowing hot air to be distributed through holes in the wingtip surface, ensuring effective de-icing regardless of the wingtip's position.
The system enables efficient de-icing of the wingtip in both flight and ground positions, maintaining de-icing effectiveness by ensuring consistent hot air delivery through the conduit, even when the wingtip is raised.
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Abstract
Description
Title of the invention: Wing for an aircraft incorporating a de-icing system technical field
[0001] The present invention relates to a wing for an aircraft comprising a fixed wing and a wingtip mounted hinged to the end of the fixed wing and a de-icing system integrated into the wingtip. The present invention also relates to an aircraft comprising at least one such wing. PREVIOUS STATE OF THE ART
[0002] To save space, particularly during maneuvers on a tarmac, some aircraft have folding wings. Such a wing comprises a fixed wing with a proximal end attached to the fuselage and a distal end, and a wingtip with a distal end and a proximal end hinged to the fixed wing at the distal end of said fixed wing. Typically, when the aircraft is on the ground, the wingtip is raised and positioned above the distal end of the fixed wing.
[0003] In the event of frost on the wings, a de-icing fluid is sprayed over them. However, when the wingtip is raised, the de-icing fluid may have difficulty reaching the entire surface of the wingtip, particularly the upper surface (extrados) which is now underneath. This can delay the wingtip's de-icing. Furthermore, when the wingtip is raised, the de-icing fluid runs down the wingtip due to its vertical orientation, limiting its time on the wingtip and therefore its effectiveness, which can reduce the fluid's de-icing capacity.
[0004] It is therefore desirable to find an arrangement which provides improvements and allows de-icing of the wingtip, even when it is raised. Description of the invention
[0005] An object of the present invention is to provide a wing which comprises a fixed wing and an articulated wingtip and which is equipped with a de-icing system disposed on the wingtip.
[0006] To this end, a wing for an aircraft is proposed, said wing comprising:
[0007] - a fixed wing having a proximal end intended to be fixed to a structure of the aircraft and a distal end,
[0008] - a wingtip having a distal end and a proximal end mounted articulated at the distal end of the fixed wing, where the wingtip is movable between a lowered position, in which the wingtip extends the fixed wing, and a raised position, in which the wingtip is raised, and
[0009] - a defrosting system comprising a conduit circulating inside the end wing, a fluidly connected supply duct to said duct and intended to be fluidly connected to a hot air source, wherein said supply duct has an intermediate duct which passes from the distal end of the fixed wing to the proximal end of the wingtip and control means arranged to regulate the quantity of hot air passing through the supply duct.
[0010] With such an arrangement the wingtip can be de-iced in flight or on the ground, including when the wingtip is in the raised position.
[0011] Advantageously, at the level of its lower surface, the wingtip is pierced with holes through which the conduit opens to the outside of the wingtip.
[0012] According to a particular embodiment, the intermediate conduit comprises a first intermediate portion mounted at the distal end of the fixed wing, a second intermediate portion mounted at the proximal end of the wingtip and an intermediate arc-shaped section, a first end of which is articulated at the level of the first intermediate portion and a second end of which is articulated at the level of the second intermediate portion.
[0013] According to a particular embodiment, the intermediate conduit comprises a first intermediate portion mounted at the distal end of the fixed wing, a second intermediate portion mounted at the proximal end of the wingtip and at least two intermediate sections in an arc of a circle, where a first intermediate section has a first end mounted articulated at the level of the first intermediate portion, where a last intermediate section has a second end mounted articulated at the level of the second intermediate portion, where for two adjacent intermediate sections, the lower-ranking intermediate section has a second end mounted articulated at the level of a first end of the higher-ranking intermediate section.
[0014] Advantageously, for each intermediate section, the supply conduit comprises an arm whose distal end is fixed to the intermediate section and whose proximal end is mounted to rotate freely around the hinge axis.
[0015] According to a particular embodiment, the intermediate conduit takes the form of a bellows tube, the first end of which is mounted at the distal end of the fixed wing and the second end of which is mounted at the proximal end of the wingtip.
[0016] According to a particular embodiment, the intermediate conduit comprises a flexible inner tube, a first end of which is mounted at the distal end of the fixed wing and a second end of which is mounted at at the level of the proximal end of the wingtip and a protective tube, one end of which is mounted at the level of the distal end of the fixed wing and the other end of which is mounted at the level of the proximal end of the wingtip, and into which the inner tube is inserted, where the protective tube is a telescopic tube.
[0017] According to a particular embodiment, the intermediate conduit comprises a first intermediate portion mounted at the distal end of the fixed wing and a second intermediate portion mounted at the proximal end of the wingtip, each intermediate portion has a circular arc portion coaxial with respect to the hinge axis and a circular arc portion is housed in the other circular arc portion.
[0018] The invention also proposes an aircraft comprising a structure and a wing according to one of the preceding variants, where the proximal end of the fixed wing is attached to the structure. Brief description of the drawings
[0019] The features of the invention mentioned above, as well as others, will become clearer upon reading the following description of an exemplary embodiment, said description being made in relation to the accompanying drawings, among which:
[0020] [Fig-1] is a top view of an aircraft comprising a wing according to the invention,
[0021] [Fig.2] is a schematic perspective representation of a wing according to the invention with the wingtip in the lowered position,
[0022] [Fig.3] is a front view of the wing according to the invention with the wingtip in position raised with a defrosting system according to the invention,
[0023] [Fig.4] is a front and cross-sectional view of an intermediate pipe along a first method of embodiment and implementation in the defrosting system according to the invention and in the lowered position,
[0024] [Fig.5] is a front and cross-sectional view of the intermediate conduit of the [Fig.4] in raised position
[0025] [Fig.6] is a front and cross-sectional view of an intermediate pipe along a second embodiment and implementation in the defrosting system according to the invention and in a lowered position,
[0026] [Fig.7] is a front and cross-sectional view of the intermediate conduit of the [Fig.6] in raised position
[0027] [Fig.8] is a front view of an intermediate pipe according to a third mode of implementation and installation in the defrosting system according to the invention and in the raised position,
[0028] [Fig.9] is a front view of an intermediate conduit according to a fourth embodiment and implemented in the defrosting system according to the invention and in the raised position, and
[0029] [Fig. 10] is a front and cross-sectional view of an intermediate conduit according to a fifth embodiment and implemented in the defrosting system according to the invention and in a lowered position.
[0030] DETAILED STATEMENT OF IMPROVEMENTS
[0031] Fig. 1 shows an aircraft 10 comprising a fuselage 12 on either side of which a wing 100 is fixed. Here, each wing 100 supports an engine 14.
[0032] In the following description, and by convention, X is called the longitudinal axis of the aircraft 10 oriented positively in the direction of advancement of the aircraft 10, Y is called the transverse axis which is horizontal when the aircraft 10 is on the ground, and Z is called the vertical axis when the aircraft 10 is on the ground, these three directions X, Y and Z being orthogonal to each other.
[0033] Fig. 2 shows a wing 100 according to the invention which comprises a fixed wing 102 and a wingtip 104 mounted articulated on the fixed wing 102. The fixed wing 102 is globally horizontal.
[0034] More precisely, the fixed wing 102 has a proximal end 102a which is fixed to a structure of the aircraft 10, such as for example a structure of the fuselage 12. The fixed wing 102 also has a distal end 102b which is opposite the proximal end 102a.
[0035] The wingtip 104 has a proximal end 104a which is mounted articulated at the distal end 102b of the fixed wing 102. The wingtip 104 also has a distal end 104b which is opposite the proximal end 104a and which forms the free end of the wing 100.
[0036] Conventionally the fixed wing 102 and the wingtip 104 each have a leading edge 108a, 110a and a trailing edge 108b, 110b.
[0037] As shown in [Fig.3], the wingtip 104 is mounted on the fixed wing 102 by means of a hinge 112 which provides the articulation of the wingtip 104 with respect to the fixed wing 102. The articulation is a rotation around a hinge axis X' which is globally parallel to the longitudinal axis X.
[0038] The wingtip 104 is movable between a lowered position ([Fig. 2]) and a raised position ([Fig. 3]) and vice versa. Conventionally, the wing 100 incorporates the mechanical means necessary for moving the wingtip 104, such as a motorized system. Such mechanical means are not described in more detail, as they are not part of the invention and a person skilled in the art can use various known means.
[0039] In the lowered position, the wingtip 104 extends the fixed wing 102 to form the wing 100 in the flight position. In this position, the proximal end 104a of the wingtip 104 extends the distal end 102b of the fixed wing 102 and the wingtip 104 is also generally horizontal.
[0040] In the raised position, the wingtip 104 is tilted upwards, i.e. the distal end 104b is lifted and the wingtip 104 is raised.
[0041] The rotation of the wingtip 104 is classically around 90°, but a different angle is also possible.
[0042] The wing 100 finally includes a de-icing system 150 which ensures the de-icing of the wingtip 104 and more particularly of its upper surface and its leading edge 110a.
[0043] As shown in [Fig.3], the de-icing system 150 includes a conduit 152 (seen in dotted lines on [Fig.3]) running inside the wingtip 104 as close as possible to the area to be de-iced which is represented on Figs. 1 to 3 by the hatched area.
[0044] According to a particular embodiment, the duct 152 opens to the outside of the wingtip 104 through holes 153 which are made on the underside of the wingtip 104 (in [Fig. 2], the holes are seen through the transparent material). These holes 153 allow the circulation of hot air by ensuring the evacuation of the hot air circulating in the duct 152 and thus ensuring the de-icing of the desired area on the wingtip 104.
[0045] The de-icing system 150 also includes a supply line 154 which has a first end fluidly connected to the duct 152 and a second end fluidly connected to a hot air source 16 of the aircraft 10 such as, for example, an engine duct 14. Hot air can also be drawn from the aircraft engines 14 and conveyed to the duct 152, by means of the supply line 154. A regulating valve allows control of the flow of hot air conveyed by the line 154.
[0046] The supply line 154 thus extends, in part, into the fixed wing 102 and passes through the gap at the hinge 112 to join the conduit 152 to which it is fluidically connected to carry the hot air. To this end, the supply line 154 has an intermediate conduit 154a which runs from the distal end 102b of the fixed wing 102 to the proximal end 104a of the wingtip 104.
[0047] The intermediate pipe 154a is flexible to follow the movement of the wingtip 104, and the hot air thus reaches the wingtip 104 whether it is in the lowered or raised position. Therefore, with this de-icing system 150, it is possible to ensure the de-icing of the wingtip 104 in flight or on the ground, including when the wingtip 104 is in the raised position. In the embodiment of [Fig. 3], the intermediate pipe 154a takes the form of a flexible tube, one end of which is mounted at the distal end 102b of the fixed wing 102 and of which a second end is mounted at the proximal end 104a of the wingtip 104.
[0048] To control the quantity of hot air passing through the supply duct 154, the defrosting system 150 also includes control means 156 arranged to regulate said quantity. These control means 156 take, for example, the form of a solenoid valve controlled remotely and according to requirements.
[0049] In the embodiment of the invention shown in [Fig.3], the control means 156 are located at the level of the fixed wing 102 but they can be located at the level of the wingtip 104 or at the level of the hot air source 16 or the engines 14.
[0050] Figures 4 and 5 show a first embodiment of the conduction Intermediate 154a. In this embodiment, the intermediate duct 154a comprises a first intermediate portion 254a, mounted at the distal end 102b of the fixed wing 102 and preferably rigid, and a second intermediate portion 254b, mounted at the proximal end 104a of the wingtip 104 and preferably rigid. Each intermediate portion 254a-b is a hollow tube through which hot air passes. The first intermediate portion 254a extends the portion of the supply duct 154 that is in the fixed wing 102, and the second intermediate portion 254b extends the duct 152.
[0051] The intermediate conduit 154 also includes an intermediate section 254c in the form of an arc, the first end of which is hinged to the first intermediate portion 254a and the second end of which is hinged to the second intermediate portion 254b. The first end of the intermediate section 254c is movable within the first intermediate portion 254a and the second end of the intermediate section 254c is movable within the second intermediate portion 254b. The intermediate section 254c is also a hollow tube.
[0052] Due to the arched shape of the intermediate section 254c, the transition from the lowered position to the raised position consists of a rotation of the intermediate section 254c relative to the first intermediate portion 254a and the rotation of the second intermediate portion 254b relative to the intermediate section 254c. A different nesting is also possible.
[0053] Each rotation is globally centered on the hinge axis X' and is limited by stops 256 of the intermediate section 254c which, in the raised position, abut against counter-stops 258 of the first intermediate portion 254a and the second intermediate portion 254b. In the embodiment of the invention shown in [Fig. 5], the rotation of the intermediate section 254c and the rotation of the second intermediate portion 254b are each of the order of 45° to obtain a raised position at 90°.
[0054] To ensure sealing, a seal 260, in particular an O-ring, is disposed between each intermediate portion 254a-b and the intermediate section 254c, bearing against the outer wall of the intermediate section 254c. Here, each seal 260 is housed in a groove formed in the buttresses 258.
[0055] To assist the rotation of the intermediate section 254c about the hinge axis X', the intermediate conduit 154 has an arm 253 whose distal end is fixed to the intermediate section 254c and whose proximal end is mounted to rotate freely about the hinge axis X'. In particular, here, the proximal end is mounted to rotate freely about a shaft coaxial with the hinge axis X', where the shaft is mounted fixed relative to the first intermediate portion 254a, i.e., relative to the fixed wing 102.
[0056] Arrows 13 show the flow of hot air.
[0057] Figures 6 and 7 show a second embodiment of the intermediate conduit 154a. In this embodiment, the intermediate conduit 154a comprises a first intermediate portion 354a, which is mounted at the distal end 102b of the fixed wing 102 and is preferably rigid, and a second intermediate portion 354b, which is mounted at the proximal end 104a of the wingtip 104 and is preferably rigid. Each intermediate portion 354a-b is a hollow tube through which hot air passes. The first intermediate portion 354a extends the portion of the supply conduit 154 that is in the fixed wing 102, and the second intermediate portion 354b extends the conduit 152.
[0058] The intermediate conduit 154 also includes at least two intermediate sections 354c-d. Here, there are two intermediate sections, but it is possible to have more if needed.
[0059] Each intermediate section 354c-d is in the form of a circular arc.
[0060] A first intermediate section 354c has a first end mounted articulated at the level of the first intermediate portion 354a and a last (here the second) intermediate section 354d has a second end mounted articulated at the level of the second intermediate portion 354b.
[0061] For two adjacent intermediate sections 354c-d, the lower-rank intermediate section 354c has a second end mounted and hinged at the level of a first end of the higher-rank intermediate section 354d.
[0062] The first end of the first intermediate section 354c is movably mounted inside the first intermediate portion 354a, and the second end of the last intermediate section 354d is movably mounted inside the second intermediate portion 354b. Each second end of an intermediate section The lower-ranking 354c is movably mounted inside the first end of the next-higher-ranking intermediate section 354d. The intermediate sections 354c-d thus form a telescopic assembly. A different nesting arrangement is also possible.
[0063] Each intermediate section 354c-d is also a hollow tube.
[0064] Due to the arched shape of each intermediate section 354c-d, the transition from the lowered position to the raised position consists of a rotation of each intermediate section 354c-d relative to the first intermediate portion 354a or relative to the intermediate section 354c of just lower rank and the rotation of the second intermediate portion 354b relative to the last intermediate section 354d.
[0065] Each rotation is globally centered on the hinge axis X' and is limited by stops 356 of each intermediate section 354c-d which, in the raised position, abut against counter-stops 358 of the first intermediate portion 354a, the second intermediate portion 354b, and the next higher intermediate section 354d. In the embodiment of the invention shown in [Fig. 7], the overall rotation of the intermediate sections 354c-d is approximately 45° and the rotation of the second intermediate portion 354b is approximately 90° to obtain a raised position at 90°.
[0066] To ensure sealing, a seal 360, in particular an O-ring, is disposed against the outer wall of each intermediate section 354c-d, bearing against the outer wall of said intermediate section 354c-d. Here, each seal 360 is housed in a groove formed in the buttresses 358.
[0067] As before, to assist the rotation of each intermediate section 354c-d about the hinge axis X', the intermediate conduit 154 has, for each intermediate section 354c-d, an arm (not shown for clarity in the Figs, but it has a shape similar to that of [Fig. 4]) whose distal end is fixed to the intermediate section 354c-d and whose proximal end is mounted to rotate freely about the hinge axis X'. In particular, each proximal end is mounted to rotate freely about a shaft coaxial with the hinge axis X', where the shaft is mounted fixed relative to the first intermediate portion 354a, i.e., relative to the fixed wing 102.
[0068] Arrows 13 show the flow of hot air.
[0069] Figure 8 shows a third embodiment of the intermediate conduit 154a. In this embodiment, the intermediate conduit 154a takes the form of a bellows tube 454, one end of which is mounted at the distal end 102b of the fixed wing 102, and the other end of which is mounted at the proximal end 104a of the wingtip 104. The bellows tube 454 is a hollow tube through which hot air passes.
[0070] The first end extends the portion of the supply line 154 which is in the fixed wing 102 and the second end extends the line 152.
[0071] Figure 9 shows a fourth embodiment of the intermediate conduit 154a. In this embodiment, the intermediate conduit 154a comprises a flexible inner tube 554a (here in dotted line) of which a first end is mounted at the distal end 102b of the fixed wing 102 and a second end is mounted at the proximal end 104a of the wingtip 104 and a protective tube 554b of which a first end is mounted at the distal end 102b of the fixed wing 102 and a second end is mounted at the proximal end 104a of the wingtip 104.
[0072] The inner tube 554a is inserted into the protective tube 554b, which is a telescopic tube made up of several generally frustoconical rings, where the smaller diameter end of each ring is inserted into the larger diameter end of the adjacent ring. The inner tube 554a ensures the sealing of the device. The protective tube 554b also allows, if necessary, for the containment of the expansion of the inner tube 554a.
[0073] Figure 10 shows a fifth embodiment of the intermediate conduit 154a. In this embodiment, the intermediate conduit 154a comprises a first intermediate portion 654a, which is mounted at the distal end 102b of the fixed wing 102 and is preferably rigid, and a second intermediate portion 654b, which is mounted at the proximal end 104a of the wingtip 104 and is preferably rigid. Each intermediate portion 654a-b is a hollow tube through which hot air passes. The first intermediate portion 654a extends the portion of the supply conduit 154 that is in the fixed wing 102, and the second intermediate portion 654b extends the conduit 152.
[0074] Each intermediate portion 654a-b has a circular arc part, and one of the circular arc parts (here, the second intermediate portion 654b) is housed within the other circular arc part (here, the first intermediate portion 654a). A reverse nesting is also possible.
[0075] The two circular arc parts are coaxial with respect to the hinge axis X'.
[0076] Thus, during the rotation of the wingtip 104 from the lowered position to the position raised, the second intermediate portion 654b pivots around the hinge axis X' inside the first intermediate portion 654a.
[0077] The rotation is limited by stops 256 of one of the intermediate portions 654b-a which, in the raised position, come against counter-stops 258 of the other intermediate portion 654a-b.
[0078] To ensure sealing, a seal 260, in particular an O-ring, is disposed between each intermediate portion 654a-b, bearing against the outer wall of the intermediate portion 654b which is inside. Here, each seal 260 is housed in a groove formed in the buttresses 258 of the first intermediate portion 654a.
Claims
Demands
1. A wing (100) for an aircraft (10), said wing (100) comprising: - a fixed wing (102) having a proximal end (102a) for attachment to a structure of the aircraft (10) and a distal end (102b), - a wingtip (104) having a distal end (104b) and a proximal end (104a) hinged to the distal end (102b) of the fixed wing (102), wherein the wingtip (104) is movable between a lowered position, in which the wingtip (104) extends the fixed wing (102), and a raised position, in which the wingtip (104) is raised, and - a de-icing system (150) comprising a duct (152) running inside the wingtip (104), a conduit supply (154) fluidly connected to said conduit (152) and intended to be fluidly connected to a hot air source (16),where said supply line (154) has an intermediate line (154a) which runs from the distal end (102b) of the fixed wing (102) to the proximal end (104a) of the wingtip (104) and control means (156) arranged to regulate the amount of hot air passing through the supply line (154).
2. Wing (100) according to claim 1, characterized in that at the level of its lower surface, the wingtip (104) is pierced with holes (153) through which the conduit (152) opens to the outside of the wingtip (104).
3. Wing (100) according to any one of claims 1 or 2, characterized in that the intermediate conduit (154a) comprises a first intermediate portion (254a) mounted at the distal end (102b) of the fixed wing (102), a second intermediate portion (254b) mounted at the proximal end (104a) of the wingtip (104) and an intermediate section (254c) in the form of an arc of a circle, a first end of which is mounted articulated at the level of the first intermediate portion (254a) and a second end of which is mounted articulated at the level of the second intermediate portion (254b).
4. Wing (100) according to any one of claims 1 or 2, characterized in that the intermediate conduit (154a) comprises a first intermediate portion (354a) mounted at the distal end (102b) of the fixed wing (102), a second intermediate portion (354b) mounted at the proximal end (104a) of the wingtip (104) and at least two intermediate sections (354c-d) in an arc of a circle, where a first intermediate section (354c) has a first mounted end articulated at the level of the first intermediate portion (354a), where a last intermediate section (354d) has a second mounted end articulated at the level of the second intermediate portion (354b), where for two neighboring intermediate sections (354c-d), the lower-ranking intermediate section (354c) has a second mounted end articulated at the level of a first end of the higher-ranking intermediate section (354d).
5. Wing (100) according to any one of claims 3 or 4, characterized in that for each intermediate section (254c, 354c-d), the supply conduit (154) comprises an arm (253) whose distal end is fixed to the intermediate section (254c) and whose proximal end is mounted to rotate freely around the hinge axis (X').
6. Wing (100) according to any one of claims 1 or 2, characterized in that the intermediate conduit (154a) takes the form of a bellows tube (454) of which a first end is mounted at the level of the distal end (102b) of the fixed wing (102) and of which a second end is mounted at the level of the proximal end (104a) of the wingtip (104).
7. Wing (100) according to any one of claims 1 or 2, characterized in that the intermediate conduit (154a) comprises a flexible inner tube (554a) having a first end mounted at the distal end (102b) of the fixed wing (102) and a second end mounted at the proximal end (104a) of the wingtip (104) and a protective tube (554b) having a first end mounted at the distal end (102b) of the fixed wing (102) and a second end mounted at the proximal end (104a) of the wingtip (104) and into which the inner tube (554a) is inserted, wherein the protective tube (554b) is a telescopic tube.
8. Wing (100) according to any one of claims 1 or 2, characterized in that the intermediate conduit (154a) comprises a first intermediate portion (654a) mounted at the distal end (102b) of the fixed wing (102) and a second intermediate portion (654b) 13 mounted at the proximal end (104a) of the wingtip (104), in that each intermediate portion (654a-b) has a circular arc part coaxial with respect to the hinge axis (X') and in that one circular arc part is housed in the other circular arc part.
9. Aircraft (10) comprising a structure and a wing (100) according to any one of the preceding claims, wherein the proximal end (102a) of the fixed wing (102) is fixed to the structure.
Citation Information
Patent Citations
De-icing system for an aircraft
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Movable wing tip
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