Patent Application
20240343380
This application claims priority to European Patent Application Number EP 23167378.1, filed Apr. 11, 2023, the entire contents of which is hereby incorporated by reference.
The present disclosure is directed toward a fairing arrangement for a high-lift mechanism of an aircraft, wherein the high-lift mechanism includes a flap to be arranged at a trailing edge of an aircraft wing and a mounting and guiding mechanism for the flap. More specifically, the disclosure is directed toward a high-lift system, an aircraft wing and an aircraft comprising such fairing arrangement.
With regard to prior art, reference is made to the following citations:
References (1) to (4) disclose a fairing arrangement for a high-lift mechanism of an aircraft, wherein the high-lift mechanism includes a flap to be arranged at a trailing edge of an aircraft wing and a mounting and guiding mechanism for the flap, the fairing arrangement comprising a flap side fairing unit and a wing side fairing unit, the flap side fairing unit comprising a flap side fairing for covering an aft part of the mounting and guiding mechanism and a flap side fairing mount for movably mounting the flap side fairing to the flap, the wing side fairing unit comprising a wing side fairing for covering a forward part of the mounting and guiding mechanism and a wing side fairing mount for mounting the wing side fairing in a rigidly fixed manner to the wing.
The present disclosure contemplates fairing arrangements with improved functionality.
The present disclosure provides a fairing arrangement for a high-lift mechanism of an aircraft, wherein the high-lift mechanism includes a flap to be arranged at a trailing edge of an aircraft wing and a mounting and guiding mechanism for the flap. The fairing arrangement comprises a flap side fairing unit and a wing side fairing unit. The flap side fairing unit comprises a flap side fairing for covering an aft part of the mounting and guiding mechanism and a flap side fairing mount for rigidly mounting the flap side fairing to the flap. The wing side fairing unit comprises a wing side fairing for covering a forward part of the mounting and guiding mechanism and a wing side fairing mount for mounting the wing side fairing to the wing. The wing side fairing mount is configured for connecting the wing side fairing movably to the wing. For example, the wing side fairing mount is configured such that the wing side fairing mounted therewith or at least a part thereof is movable in a lateral direction. The wing side fairing mount may be configured for connecting the wing side fairing movably to the wing such that the wing side fairing is rotatable around an axis directed at least partially in a vertical direction. The wing side fairing and the flap side fairing are connected by a fairing joint allowing relative movements of the fairings during movement of the flap such that the movement of the wing side fairing relative to the wing is controlled by the movement of the flap side fairing. The fairing joint may be configured such that the rotational movement of the wing side fairing around the axis is controlled or driven by the movement of the flap side fairing. Thus, in use, the flap side fairing can be rigidly mounted to the flap for movement therewith. The movement of the flap side fairing is transferred via the fairing joint to the wing side fairing. The fairing joint has enough degrees of freedom to allow relative movements of the wing side fairing and the flap side fairing during movements of the flap.
According to an exemplary embodiment, the movable wing side fairing is mechanically coupled to the flap side fairing with the fairing joint. The movable wing side fairing may be mechanically coupled to the flap side fairing with a 5 degree of freedom joint.
The fairing joint may be configured such that it allows relative movements of the fairings in at least one or several or all of the following degrees of freedom:
The fairing joint may be configured such that it affects a common sideward movement of a rearward end portion of the wing side fairing and of a forward end portion of the flap side fairing.
The fairing joint may have five degrees of freedom.
The fairing joint may include a spherical bearing and a sliding bearing.
The spherical bearing may be mounted on one of the fairings and the sliding bearing is arranged between the spherical bearing and the other one of the fairings.
The sliding bearing may comprise a sliding pad for sliding in a plane. Alternatively, the sliding bearing comprises a piston slidable in a sliding bush and provides a further, preferably rotational, degree of freedom.
For example, the piston and/or the bush are mounted to the associated fairing in a manner rotatable about an axis essentially perpendicular to the sliding direction such as a horizontal axis essentially directed in the spanwise or lateral direction.
The wing side fairing unit may be configured such that a rear part of the wing side fairing to be engaged with the flap side fairing is movable in a limited predefined manner in a spanwise direction.
The wing side fairing mount may comprise a forward connecting mechanism configured to connect a forward part of the wing side fairing rotatably with at least one or with two degrees of freedom to the mounting and guiding mechanism.
The forward connecting mechanism may include a spherical bearing. The forward connecting mechanism may allow movement of a forward part of the wing side fairing in at least two degrees of freedom, especially by a rotation about a first axis that has at least a direction component in the vertical direction (e.g., the vertical direction is the lift direction of the wing) and by a rotation about a second axis extending or essentially extending in the flight direction.
The wing side fairing mount may comprise a rearward connecting mechanism configured to connect a rearward part of the wing side fairing such that it is movable in a spanwise direction.
The rearward connecting mechanism may include a swing strut. The rearward connecting mechanism may include a pair of parallel swing struts. The rearward connecting mechanism may include a tensile means, i.e., flexible means such as a cable or a chain. The rearward connecting mechanism may include an arrangement of a track and rollers or sliders. The rearward connecting mechanism may include an upper track and roller or slider arrangement and/or a lower track and roller or slider arrangement. The rearward connecting mechanism may include a track curved around a rotation axis of the forward connecting mechanism in combination with a set of rollers or sliders running on the track. The rearward connecting mechanism may include a linear bearing.
A forward end portion of the flap side fairing may engage into a rearward end portion of the wing side fairing in order to allow a telescopic and rotational relative movement of said fairings.
The fairing arrangement may further comprise a fixed front fairing unit configured to be rigidly fixed to the wing, wherein the wing side fairing unit is configured as intermediate movable wing side fairing unit arranged between fixed front fairing unit and the flap side fairing unit.
According to an exemplary embodiment, a high-lift system for an aircraft is provided having a high-lift mechanism including a flap to be arranged at a trailing edge of an aircraft wing and a mounting and guiding mechanism for the flap (also called flap support in the prior art), and a fairing arrangement according to any of the aforementioned embodiments.
According to an exemplary embodiment, an aircraft wing is provided comprising such a high-lift system and/or a fairing arrangement according to any of the aforementioned embodiments.
According to an exemplary embodiment, an aircraft is provided comprising a wing arrangement including such a wing and/or such a high-lift system and/or a fairing arrangement according to any of the aforementioned embodiments.
The disclosure lies on the technical field of aircraft high-lift systems and especially relates to fairings of such high-lift systems.
Exemplary embodiments propose improved fairing kinematics for a variable shape trailing edge.
Exemplary embodiments relate to a type of fairing arrangement that is kinematically configured to translate and rotate.
In known fairing solutions such as mentioned above, a forward part of the fairing is rigidly assembled to the wing and the aft part of the fairing has a hinged connection to a flap support beam.
Exemplary embodiments provide at least one, several or all of the following advantages:
The fairing kinematic principle according to exemplary embodiments provide at least one, several or all of the following benefits:
Exemplary embodiments are related to an aircraft wing, in the area of high-lift devices like flaps. Flaps are normally mounted on flap support structures, which are on most aircrafts covered by fairings. Exemplary embodiments provide a mechanism, which is used to deploy fairing-movable-parts with a simple and compact kinematics with a lot of benefits on aircraft level. Exemplary embodiments relate to a high-lift trailing edge device, where each flap is supported by two or more tracks. For aerodynamic reasons the tracks are covered with a fairing arrangement. During deployment and retraction of the flaps, fairings of the fairing arrangement are driven by the motion of the flap. As in most commercial airliners, a wing side fairing of the fairing arrangement is not rigidly fixed to the wing, especially the wing box, but is mounted such that a rear end portion thereof can move laterally. Especially, the wing side fairing can conduct a rotational movement about a vertical axis.
According to an exemplary embodiment, a fairing, which comprises a forward movable fairing (referred to as wing side fairing), and a rearward fairing attached to the flap (referred to as flap side fairing) are disclosed. The forward-movable-fairing (FMF) is rotating around a vertical axis, which is mounted on the flap support structure, but this motion is not limited to rotations for the forward fairing.
According to an exemplary embodiment, the rearward fairing (RF) is directly attached to the flap, so just follows the flap motion. The rotation or other movement of the forward movable fairing (FMF) will be controlled by the rearward fairing (RF) with a 5 degree of freedom joint (5 DoF). The principle only needs very few parts and also enables high-lift and high-speed operation (VC/DFS) without creating significant steps in the split area during operation.
According to an exemplary embodiment, the mechanism principle works such that a spherical bearing (3 DoF) is fixedly attached to the movable wing side fairing, and a sliding pad (with 2 DoF) is fixed to the rearward flap side fairing. Overall, the degrees-of-freedom at the joint are in sum 5.
Another possibility is to invert the location of the spherical bearing to the rearward flap side fairing (3 DoF) and fix it to this location to the structure of the flap side fairing. In this case 2 further DoF are provided in the movable wing side fairing, which can be done by a sliding bearing designed as pads (2 DoF) or two translating joints (2 DoF), or one translating joint and adjacent rotational link (2 DoF), or two adjacent rotational links (2 DoF).
A benefit of the exemplary embodiments is that the rearward fairing (RF—flap side fairing) controls the lateral motion of the forward fairing (wing side fairing) in high-lift and high-speed operation (VC/DFS) by minimizing the steps out of wind in the split line.
Furthermore, an exemplary embodiment enables a very good sealing high-speed and low speed, even if a lot of fowler-motion is implemented in the flap kinematics. The forward-movable-fairing loads are also transferred via the 5 DoF-joint to the rearward fairing.
Between the flap and the flap side fairing no elastomer sealing is required, because the two parts are attached to each other; this stiffens the structure and reduces the overall weight of the fairing. In use, the flap side fairing of the fairing arrangement is attached to the flap which simplifies the fairing kinematics considerably (no need of operating rod, structure frames, side load stay, and a lot of sealings). Also a very good sealing is provided in high-speed and low-speed in the split area, without huge steps.
According to an exemplary embodiment, a location of the 5 DoF joint under a flap-support-structure (FSS, referred to as mounting and guiding mechanism above) is also beneficial in terms of minimizing the relative motions, between the wing side and the flap side fairing. Especially for the system installation (SI) routing, which can be directly fixed to the joint elements and avoids an entrapment of the wires in the fairing split lines.
For an understanding of embodiments of the disclosure, reference is now made to the following description taken in conjunction with the accompanying drawings, in which:
Some embodiments will now be described with reference to the Figures.
An aircraft 10 as shown in
According to an exemplary embodiment, the wing 12 has a variable shape trailing edge functionality (VSTE) where the trailing edge 16 has a variable shape and can be deformed for different flight situations.
a,
2
b,
2
c,
3
a,
3
b, and 3c show an embodiment of the fairing arrangement 26 in different flap positions, wherein
Referring to
The fairing arrangement 26 comprises a flap side fairing unit 28 and a wing side fairing unit 30. As seen in flight direction of the aircraft 10, the flap side fairing unit 28 is an aft fairing unit and the wing side fairing unit is a forward fairing unit.
The flap side fairing unit 28 comprises a flap side fairing 32 for covering an aft part of the mounting and guiding mechanism 24 and a flap side fairing mount 34 for mounting the flap side fairing 32 to the flap 22. In the embodiments shown, the flap side fairing mount 34 is configured to mount the flap side fairing 32 rigidly to the flap 22. For example, the shell of the flap side fairing 32 may be mounted with usual bolts, rivets or fasteners (not shown) to the flap 22.
The wing side fairing unit 30 comprises a wing side fairing 36 for covering a forward part of the mounting and guiding mechanism 24 and a wing side fairing mount 38 for mounting the wing side fairing 36 to the wing. The wing side fairing mount 38 is configured to movably connect the wing side fairing 36 to the wing 12 or the front part of the mounting and guiding mechanism 24 which is attached to the wing 12. In some embodiments (not shown), the wing side fairing mount 38 connects the wing side fairing 36 such that it is shiftable in a lateral direction.
According to an exemplary embodiment, the wing side fairing mount 38 is configured to connect the wing side fairing 36 to the wing 12 or the front part of the mounting and guiding mechanism 24 which is attached to the wing 12 such that it is rotatable around an essentially vertical axis 39 directed at least with its largest direction component in a vertical direction. Here, the vertical direction is the direction essentially perpendicular to the spanwise and chordwise directions of the wing 12, i.e., the direction of lift.
Although not shown in
As further shown in
In the following, the exemplary embodiment of the wing side fairing mount 38 are described referring to
The forward connecting mechanism 40 is configured to connect a forward part of the wing side fairing 36 rotatably with one degree of freedom or with two degrees of freedom to the mounting and guiding mechanism 24.
In an embodiment not shown, the forward connecting mechanism 40 just has a simple bearing allowing rotation of the wing side fairing around the essentially vertical axis 39.
In the exemplary embodiments shown in
The rearward connecting mechanism 42 is configured to allow a movement of the rearward part of the wing side fairing 36 in a spanwise direction during the rotational movement about the essentially vertical axis 39. Several possible designs of the rearward connecting mechanism 42 are provided in the first to fourth embodiment as shown in
In an exemplary embodiment as shown in
The swing struts 60.1, 60.2 are equipped with multi-axis bearings such as spherical bearings 61 at their ends in order to connect the strut ends movably to the track member 52 and the wing side fairing 36, respectively.
As a variation (not shown) the struts 60.1, 60.2 can be replaced by flexible tensile means or flexible elements like steel cables in combination with a roller or linear bearing below the track member 52.
In an exemplary embodiment shown in
In an exemplary embodiment shown in
In an exemplary embodiment shown in
In other words, a forward fairing for covering a front part of the mounting and guiding mechanism 24 is split into a fixed fairing 76 and the wing side fairing 36, here configured as an intermediate fairing 78. The intermediate fairing 78 is mounted with the forward connecting mechanism 40 and the rearward connecting mechanism 42. In the fourth embodiment, the rearward connecting mechanism 42 includes the linear bearing 68 allowing movement of the aft part of the intermediate fairing 78 in spanwise direction for rotation of this intermediate bearing 78 about the essentially vertical axis 39, but of course the rearward connecting mechanism 42 could also have the design of any of the other embodiments as explained above.
In the following, exemplary embodiment of the fairing joint 80 are explained referring to
Depending on the kinematics of the flap movement, different movements of the wing side fairing 32 are possible. Depending on the kinematics, the fairing joint is configured such that it allows relative movements of the fairings 36, 32 in different degrees of freedom such as
In the exemplary embodiments shown, where the wing side fairing movement is a rotational movement around the axis 39 with further possible movements as mentioned above, the fairing joint 80 is configured as a 5 degree of freedom joint e.g., providing all of the above mentioned degrees of freedom. Further, the fairing joint couples the fairings 32, 36 in order to affect a common sideward movement of the rearward end portion 58 of the wing side fairing 36 and of the forward end portion 56 of the flap side fairing 32.
In some exemplary embodiments, the fairing joint 80 comprises a spherical bearing and a sliding bearing 84. The spherical bearing of the fairing joint 80 is referred to as second spherical bearing 82 in order to distinguish it from the spherical bearing 46 of the forward connecting mechanism. The second spherical bearing 82 is mounted on one of the fairings 36, 32 and the sliding bearing 84 is arranged between the second spherical bearing 82 and the other one of the fairings 36, 32. In some embodiments, the sliding bearing 84 comprises a sliding pad 86 for sliding in a plane. In some embodiments, the sliding bearing 84 comprises a piston 88 slidable in a sliding bush 90. The piston 88 and/or the bush 90 are mounted to the associated fairing 36, 32 such that they can rotate about an axis that is essentially perpendicular to the sliding direction.
In an exemplary embodiment shown in
Another possible design of the fairing joint 80 is shown in the sixth embodiment as depicted in
A similar approach is shown in the seventh embodiment of the fairing arrangement 26 as shown in
The different features of different embodiments can be combined as needed. For example, the rearward connecting mechanism 42 may comprise any combination of swing struts, tensile means, cables, linear bearings, track and roller or slider arrangements. Further, while not shown, the fairing joint 80 of any of the first to fourth embodiments may be designed as shown in any of the fifth to seventh embodiment.
A functionally improved fairing arrangement 26 for a high-lift mechanism 20 of an aircraft 10 has been described. The high-lift mechanism 20 includes a flap 22 to be arranged at a trailing edge 16 of an aircraft wing 12 and a mounting and guiding mechanism 24 for the flap 26. The fairing arrangement 26 comprises a flap side fairing unit 28 and a wing side fairing unit 30. The flap side fairing unit 28 comprises a flap side fairing 32 for covering an aft part of the mounting and guiding mechanism 24 and a flap side fairing mount 34 for mounting the flap side fairing 32 to the flap 22. The wing side fairing unit 30 comprises a wing side fairing 36 for covering a forward part of the mounting and guiding mechanism 24 and a wing side fairing mount 38 for mounting the wing side fairing 36 to the wing 12. The wing side fairing mount 38 is configured for movably connecting the wing side fairing 36 to the wing 12, such that the wing side fairing 36 is rotatable around an axis 39 directed at least partially in a vertical direction. A fairing joint 80 couples the flap side fairing 32 and the wing side fairing 36 in order to transfer movements of the flap side fairing 32 to the wing side fairing 36. Hence, a lateral or rotational movement of the wing side fairing 36 is controlled by the flap side fairing 32.
While at least one exemplary embodiment 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.
| Number | Date | Country | Kind |
|---|---|---|---|
| 23167378.1 | Apr 2023 | EP | regional |
