Fairing fastening system for an aircraft, aircraft wings and method for mounting a fairing device

Description

[0001] The invention relates to a fairing attachment system for attachment of a fairing device to a wing of an aircraft, an aircraft wing, and a method for mounting a fairing device to a wing of an aircraft.

[0002] Modern aircrafts usually comprise wings having adjustable high lift airfoil devices which can be moved rotatably and translatory relative to the wing. Such high lift airfoil devices may be e.g. flaps and / or flaperons, which combine the functions of flaps and ailerons. They are driven by adjustment mechanisms comprising high lift support structures, which are exposed to high loads during flight and usually project beyond the underside of the wing on which the adjustable high lift airfoil devices are arranged. The high lift support structures are aerodynamically enclosed or covered by fairing elements or devices. Typically, the high lift support structures are assembled to the wing with close tolerances.

[0003] US 2016 / 0340023 A1 discloses a fairing system comprising a fixed fairing portion fixed to a wing and a movable fairing portion. A flap operating mechanism comprising a flap support structure which is attached to a mounting plate is positioned within the movable fairing portion by means of a connection rod. Thereby, a movement of a wing flap will likewise cause the movable fairing portion relative to the fixed fairing portion.

[0004] US 6 598 834 B2 discloses a method and means for increasing the aerodynamic efficiency of an airfoil employed by an aircraft. The method utilizes the primary flight control surfaces contiguous to the airfoil's trailing edge and relocates these devices to novel positions. Self-adjusting push-pull rods replace conventional solid rods where necessary in combination with a re-rigging of flight control surfaces to predetermined positions.

[0005] US 4 712 752 A discloses an air dam positioned between an opening existing between the wing rear spar cavity and a flap track fairing that depends downwardly from wing to block the flow of air between the fairing and the rear spar cavity, thereby also reducing the drag on the wing. A seal member is mounted spanwise along the rearward edge of a lower wing surface to press against the nose of a retracted rear flap to limit the passage of air between the rear flap and the lower fixed wing surface.

[0006] RU 2 394 722 C1 discloses an aircraft wing flap sliding device comprising a beam rigidly secured on wing primary structure, a straight rail with carriage mounted on the beam, and a deflecting fairing and bracket rigidly coupled with wing flap. The bracket front part is articulated with a carriage that can move along straight rail of the beam. The bracket rear part is articulated with a fairing deflection crossarm. The crossarm other end is articulated with the beam tail part. A crossarm central part is coupled with deflecting fairing.

[0007] US 3 853 289 A discloses a trailing edge flap mechanism. A first linkage connects a main flap segment to the wing to move it forwardly and rearwardly while a second linkage, interconnected by a programming link with the first linkage, properly positions the main segment between and in the extended and retracted positions.

[0008] US 4 448 375 A discloses a swinging drive link pivotally connected at its lower end to a forward support for a flap. A flap mechanism fairing consists of a fixed forward segment and a movable aft segment. The movable part of the fairing is connected to the flap carriage fitting by a fairing slave link, which moves the fairing away from the flap during deployment to clear the moving mechanism.

[0009] EP 0 081 610 A1 discloses a flap member mounted to a mounting structure through a forward track mounting means and a rear link member. A movable fairing encloses the mounting structure, the forward mounting means and the rear link member. A movable fairing encloses the mounting structure, the forward mounting means and the rear link member. Pivotally connected to an intermediate portion of the rear link is a second link, which extends downwardly and rearwardly to connect pivotally at its opposite end to a rear portion of the fairing.

[0010] CN 109 278 984 A discloses an aircraft flap rail fairing wherein a fairing honeycomb is arranged in the fairing, and a plurality of connecting joints are fixed on the inner side of the fairing through bolts. The fairing is fixed on a flap track through the connection joints.

[0011] The installation of the fairing to the wing is time consuming and thus leads to relatively high costs, as the position and the orientation of the high lift support structure relative to the wing needs exactly to be considered when the fairing is mounted. This is quite often particularly difficult because of the high number of connections to the wingbox.

[0012] It is the object of the invention to allow a quicker installation of a fairing to a wing, to provide high rates when equipping wings with flaps, and to reduce lead time.

[0013] The object is achieved by the fairing attachment system according to claim 1, the aircraft wing according to claim 10, and the method for mounting a fairing device to a wing of an aircraft according to claim 11.

[0014] The invention provides a fairing attachment system for a wing of an aircraft, the fairing attachment system comprising a high lift support structure configured for movable supporting a high-lift airfoil element of a wing of an aircraft relative to the wing; a fairing device extending in a lengthwise direction, configured for providing an aerodynamic cover or housing of the high lift support structure when attached to a surface of the wing, wherein the fairing device comprises a fixed fairing element and a movable fairing element which can be moved by the high lift support structure; the fairing attachment system further comprising an adjustable attachment element configured for attachment of the fixed fairing element to the high lift support structure, wherein the adjustable attachment element is elongated and adjustable in length in order to compensate tolerances of the high lift support structure relative to the wing during assembly.

[0015] The invention provides a fairing to wing connection which allows a quick installation of a fairing to a wing independently from the position and orientation of the high lift support structure relatively to the wing. High rates capable equipping of the flap on the wing and reducing cost and lead time in the final assembly line are achieved. Moreover, the invention enables modular installation of high lift devices like e.g. flaps and flaperons with minimizing the number of connections to the wingbox, thus reducing complexity of installation. In particular, fairing installation independently from the high lift support structure is achieved. The fairing attachment system is designed for attachment of the fairing device to the aircraft.

[0016] The high lift support structure is e.g. configured for movable attachment to the wing. In particular, the high lift airfoil element may e.g. be a flap or a flaperon.

[0017] Preferably, the adjustable attachment element is configured for being pivotally mounted to the high lift support structure about a pivot axis.

[0018] Preferably, at least a component of the pivot axis of the pivotally mounted adjustable attachment element extends in the lengthwise direction of the fairing device.

[0019] Preferably, the fairing attachment system further comprises a support element configured for supporting the fairing device at the wing at a position distant from the adjustable attachment element in the lengthwise direction of the fairing device.

[0020] Preferably, the support element provides a rotational degree of freedom, wherein the rotation axis of the support element is parallel to the pivot axis of the adjustable attachment element.

[0021] Preferably, a second pivot axis of the adjustable attachment element extends in the spanwise direction of the wing.

[0022] Preferably, the fairing attachment system further comprises a seal element configured for being mounted between the fairing device and the wing, the seal advantageously being compressible by adjustment of the adjustable attachment element, e.g. in order to control a gap between the fairing device and the wing.

[0023] The fairing device comprises a fixed fairing element and a movable fairing element which can be moved by the high lift support structure e.g. relative to the fixed fairing element, wherein the adjustable attachment element is configured for attachment of the movable fairing element to the high lift support structure.

[0024] Preferably, the adjustable fairing element is configured as a strut for an aft attachment of the fairing device.

[0025] Preferably, the support element is configured as a bracket for providing a front attachment of the fairing device.

[0026] According to an aspect of the invention, an aircraft wing comprising a high lift airfoil arrangement, a fairing device and a fairing attachment system according to the invention is provided.

[0027] According to a further aspect of the invention, a method for mounting a fairing device to a wing of an aircraft is provided, wherein a fairing attachment system according to the invention is used.

[0028] Embodiments of the invention are described in more detail with reference to the accompanying drawings. In the drawings Figs. 1 depicts a wing section with a fairing attachment system according to a preferred embodiment of the invention, as a 3-dimensional partial cut view; Fig. 2 depicts a front view of the fairing attachment system shown in Fig. 1, with a support rib in a nominal position; Fig. 3 depicts a front view of the fairing attachment system shown in Fig. 1, wherein the support rib is misaligned due to build tolerances; and Fig. 4 depicts the fairing attachment system shown in Fig. 1, wherein a rotational degree of freedom provided by a support element and a length adjustment of an adjustable attachment element are indicated as arrows.

[0029] Figure 1 depicts a section of a wing 10 comprising a fairing attachment system according to a preferred embodiment of the invention. The fairing attachment system comprises a high lift support structure 11, which is configured as a kinematic support rib and designed for supporting and moving a high lift airfoil element designed as a flap 17 of wing 10. It further comprises a fairing device 12 which forms an aerodynamic housing covering the kinematic support rib 11 at the underside 13 of wing 10. Further, the fairing attachment system comprises an adjustable attachment element 14 realized by a strut for attaching the fairing device 12 to the high lift support structure 11. The attachment element or strut 14 is longitudinally extending and adjustable in length in order to compensate tolerances of the high lift support structure 11 relative to the wing 10 during assembly.

[0030] The fairing device 12 extends in a lengthwise direction X which corresponds to the longitudinal axis of the aircraft and the wing 10. It comprises a fixed fairing element 15 which forms a forward portion of the fairing device 12, and a movable fairing element 5, which forms an aft portion of the fairing device 12.

[0031] The wing 10 comprises flap 17 as a high-lift airfoil element located at the trailing edge of the wing 10. Flap 17 is mechanically connected to the distal end 18 of an arm 19 of the kinematic support rib 11. Kinematic support rib 11 comprises a first fastener element 20 designed as a bolt and located at an end of support rib 11 opposite to the distal end 18. By the fastener element 20, kinematic support rib 11 is rotatably mounted within the wing 10. Support rib 11 comprises two support rib elements 11a, 11b formed as plates which are aligned parallel to each other with a distance between them.

[0032] Support rib 11 further comprises a second fastener element 21 designed as a bolt and located at a further portion of the arm 19 of support rib 11. By the second fastener element 21, kinematic support arm 19 is rotatably mounted below the underside 13 of the wing 10. In this way, the distal end 18 of arm 19 is able to pivot around a pivot axis extending in the spanwise direction of the wing 10, i.e. arm 19 is pivotable around the longitudinal axis of bolt 20. Thus, flap 17 connected to distal end 18 of the arm 19 is moved by the rotational movement of kinematic support rib 11, which is built as a double rib and driven by driving means not shown in the figure.

[0033] A support element 22 formed by a support bracket of the wing 10 is fixedly connected to the wing 10 and mechanically connects a portion of the fixed fairing element 15 to the wing 10, thus forming a forward attachment of the fixed fairing element 15. The forward attachment provides a rotational degree of freedom for the fixed fairing element 15, which will be explained in more detail further below. The wing fixed bracket 22 is installed during wing box assembly with close tolerances. The bracket 22 is used to attach the fairing by two bolts and serves as the forward attachment of the fixed fairing 15.

[0034] One end of strut 14 is attached to kinematic arm 19 of kinematic support rib 11 which is mechanically connected to the flap 17. The opposite end of strut 14 is attached to a support bracket 23 of the fixed fairing element 15, thus forming an aft attachment of the fixed fairing element 15. In this way, the fixed fairing element 15 is attached to the kinematic support rib 11 by strut 14.

[0035] The fairing bracket 23 or aft attachment of the fixed fairing element 15 is located at a position distant from the forward attachment 22 in the longitudinal direction X of the wing 10 and the aircraft.

[0036] Since the aft attachment of fixed fairing 15 is located on the kinematic support rib 11, the location of the support bracket 23 depends on the location of the kinematic support rib 11. Strut 14 installed at the aft attachment can be adjusted in length in order to compensate resulting tolerances of the high lift support rib 11 to wing assembly, i.e. during the final assembly line process. Thus, the final position of the fixed fairing element 15 is independent from the position of the kinematic support rib 15 which is usually installed with close tolerances.

[0037] A seal 31 located between fairing 15 and wing 10 is compressible by the adjustment of strut 14 in order to control a gap between fairing 15 and wing 10.

[0038] Referring now to Figures 2 and 3 which depict the double kinematic support rib 11, the fixed fairing element 15 of fairing device 12, and the adjustable strut 14 attached to fixed fairing element 15 as a front view. Figure 2 shows the kinematic support rib 11 in a nominal position, whereas figure 3 depicts the support rib 11 in a position where it is misaligned due to build tolerances. Both figures show the situation after installation of strut 14 in order to attach fixed fairing 15 to kinematic support rib 11.

[0039] When the support rib 11 is in its nominal position, strut 14 is installed with its nominal length, as can be seen from figure 2. However, when support rib 11 is misaligned due to build tolerances as shown in figure 3, strut 14 is adjusted in length.

[0040] Further, the end 24 of strut 14 attached to support rib 11 is pivotally installed in a support element 25 designed as a bracket and being part of support rib 11. Further, the opposite end 26 of strut 14 is also pivotally installed in support element or bracket 23 of the fixed fairing element 15.

[0041] Thus, strut 14 is able to pivot around pivot axes extending through support elements 23 and 25 perpendicular to the image plane of figures 2 and 3, i.e. in the direction X indicated in figure 1, which corresponds to the longitudinal or forward direction of the wing 10 and the aircraft. Thus, strut 14 compensates an angular mismatch due to the misalignment of support rib 11.

[0042] Figure 4 shows the length adjustment L of the strut 14 attached to fixed fairing element 15 at one side and to kinematic support rib 11 at the opposite side, as well as the rotational degree of freedom R provided by the forward attachment 22 and by the aft attachment 23 of fixed fairing element 15.

[0043] For the description of the other parts and elements shown in figures 3 and 4, reference is made to figures 1 to 3.List of reference signs:

[0044] 10wing 11high lift support structure 12fairing 13underside of the wing 14adjustable strut 15fixed fairing element 5movable fairing element 17flap 18distal end 19kinematic support arm 20first fastener element 11a, 11bsupport rib elements 21second fastener element 22support element / bracket 23support element / bracket 24end of strut 25support element / bracket 26end of strut 31seal Llength adjustment of strut Rrotational degree of freedom Xlengthwise / longitudinal direction

Claims

1. Fairing attachment system for a wing of an aircraft, comprising a high lift support structure (11) configured for movable supporting a high-lift airfoil element (17) of a wing (10) of an aircraft relative to the wing (10); a fairing device (12) extending in a lengthwise direction (X), configured for providing an aerodynamic housing of the high lift support structure (11) when attached to a surface (13) of the wing (10), wherein the fairing device (12) comprises a fixed fairing element (15) and a movable fairing element (5) which can be moved by the high lift support structure (11); characterized by an adjustable attachment element (14) configured for attachment of the fixed fairing element (15) to the high lift support structure (11), wherein the adjustable attachment element (14) is elongated and adjustable in length in order to compensate tolerances of the high lift support structure (11) relative to the wing (10) during assembly.

2. Fairing attachment system according to claim 1, wherein the adjustable attachment element (14) is configured for being pivotally mounted to the high lift support structure (11) about a pivot axis.

3. Fairing attachment system according to claim 2, wherein at least a component of the pivot axis of the adjustable attachment element (14) extends in the lengthwise direction of the fairing device (12)4. Fairing attachment system according to any of the preceding claims, further comprising a support element (22) configured for supporting the fairing device (12) at the wing (10) at a position distant from the adjustable attachment element (14) in the lengthwise direction (X) of the fairing device (12).

5. Fairing attachment system according to claims 2 and 4, wherein the support element (22) provides a rotational degree of freedom (R), wherein the rotation axis of the support element (22) is parallel to the pivot axis of the adjustable attachment element (14).

6. Fairing attachment system according to any of claims 3 to 5, wherein a second pivot axis of the adjustable attachment element (14) extends in the spanwise direction of the wing (10).

7. Fairing attachment system according to any of the preceding claims, further comprising a seal element (31) configured for being mounted between the fairing device (12) and the wing (10), the seal (31) being compressible by adjustment of the adjustable attachment element (14) in order to control a gap between the fairing device (12) and the wing (10).

8. Fairing attachment system according to any of the preceding claims, wherein the adjustable attachment element (14) is configured as a strut for attachment to an aft attachment (23) of the fairing device (12).

9. Fairing attachment system according to any of claims 4 to 8, wherein the support element (22) is configured as a bracket for providing a front attachment of the fairing device (12).

10. Aircraft wing, comprising a high lift airfoil arrangement, a fairing device (12) and a fairing attachment system according to any of the preceding claims.

11. Method for mounting a fairing device (12) to a wing (10) of an aircraft, wherein a fairing attachment system (11, 12, 14) according to any of claims 1 to 9 is used.