Multi-wing lifting surface

Abstract

A multi-spar lifting surface (30) is disclosed, comprising a multi-spar torsion box (32) having corner stiffeners (25), a movable control surface and an axial rod fitting (40). The movable control surface comprises a movable element (1), a hinged link (6.1) linked to the movable element (1), and an axial rod (7) linking the hinged link (6.1) to an aft spar (5) of the multi-spar torsion box (32). The axial rod fitting (40) is configured to link the axial rod (7) with the multi-spar torsion box (32); and comprises a longitudinal profile (10) bearing against the aft spar (5), and a lug (20) linked at one end to the longitudinal profile (10) and at the other end to the axial rod (7); the lug (20) defining a plane comprising a longitudinal axis of the axial rod (7). The multi-spar lifting surface (30) is capable of supporting lateral forces without any additional structure.

Description

Technical Field

[0001] This invention relates to a multi-spar lifting surface. Specifically, the invention relates to a multi-spar lifting surface including an assembly for transferring axial loads from a movable control surface to a multi-spar torsional box of any multi-spar lifting surface without additional internal structure. Background Technology

[0002] Any movable control surface is equipped with an articulated arm that receives loads from the control surface and transfers them to the anti-torsion box.

[0003] According to the certification specifications for large aircraft, the control surfaces and their supporting hinge brackets must be designed to withstand inertial loads acting parallel to the hinge line.

[0004] A typical solution for bearing inertial loads acting parallel to the articulation line is to install diagonal braces in a fixed structure extending from the control surface to the torsion box. These diagonal braces act on all loads outside the plane of the articulated arm, avoiding the need to reinforce the articulated arm ribs to withstand lateral forces.

[0005] The diagonal or axial bars transfer lateral loads to fixed-point fittings mounted in the rear wing beam of the anti-torsion box, which in turn transfer the loads to the fixed structure.

[0006] The structure of a conventional torsion box includes ribs, spars, stringers, and a cover. In this configuration, the "Y" component of the load transmitted by axial rod 7 is received by the rear spar 2.2, and the "X" component is received by rib 2.1. This is in Figure 2 As shown in the diagram. In order to properly introduce the load into the structure, a counterbalancing accessory 2.3 needs to be installed inside the torsion box 2.

[0007] A composite multi-spar torsion box structure is known from document WO 2008 / 132251. This structure includes at least the following structural elements: a lower surface, an upper surface, and multiple spars.

[0008] Known multi-spar torsion boxes comprise enclosed units formed by individual, facing (typically C-shaped) elements arranged together to form an enclosed unit. The web of each element forms part of a spar, and the wing of each element forms part of an upper or lower surface. Each of the formed units has multiple structural functions that, when combined, form the desired complete configuration.

[0009] In the case of a multi-wing beam torsion box structure, there are no ribs inside the torsion box that can receive the "X" component of the axial rod load.

[0010] Therefore, in order to utilize the same solution as in conventional torsion boxes, it is necessary to locally reinforce the connection points of the axial rods, for example, by positioning the elements inside the enclosed unit to transfer the load to the skin and the next spar.

[0011] However, installing any components inside a multi-spar structure is difficult because the units are enclosed, making access to the torsion box challenging. Access is only possible through the root and tip ends, and through access holes. Alternatively, cutting can be performed within the enclosed unit structure. However, such cutting weakens the units, increases assembly operations, and consequently increases cost and weight. In short, this negates the advantages of a multi-spar structure. Summary of the Invention

[0012] The object of the present invention is a lifting structure comprising a system adapted to be installed in a multi-wing torsion box configuration to support lateral forces, without requiring any additional structure inside the enclosed unit of the torsion box.

[0013] As previously mentioned, there are no ribs in the multi-spar torsion box configuration. The multi-spar torsion box includes an upper and lower surface of composite material, and multiple spars arranged between said surfaces to form a multi-unit structure, wherein the units extend along the spanwise direction at the torsion box.

[0014] Based on the above, the multi-spar lifting surface object of the present invention includes:

[0015] - A multi-spar torsion box, the multi-spar torsion box being made of composite material and comprising an upper surface and a lower surface, and a plurality of spars forming a multi-unit structure between said surfaces, the plurality of spars including a rear spar defining:

[0016] - An open unit, which opens towards the rear end of the torsion box, and is formed by a portion of the upper surface, a portion of the lower surface, and a rear wing spars, and

[0017] - A closed unit, adjacent to the open unit, and formed by an upper surface, a lower surface, a rear spar, and another spar adjacent to the rear spar.

[0018] - Movable control surfaces, including:

[0019] -Modible components

[0020] - A hinge element, comprising a hinge connector connected to a movable element, and an upper arm and a lower arm, each including a first end positioned in the hinge connector and a second end positioned in the rear spar along the lateral direction of the rear spar. The second end of the upper arm is positioned in a corner of the open unit formed by the upper surface and the rear spar, and the second end of the lower arm is positioned in a corner of the open unit formed by the lower surface and the rear spar.

[0021] - An axial rod, the axial rod including a first end located in a hinged connection and a second end located in a rear spar longitudinally away from the upper and lower arms.

[0022] According to the present invention, the multi-wing beam anti-torsion box further includes corner reinforcements formed by increasing the thickness of at least the following portions:

[0023] - The corner formed by the upper and lower surfaces and the rear wing spars of the open unit, and

[0024] - The corner of the enclosed unit formed by the upper and lower surfaces and the rear wing spars.

[0025] Furthermore, the multi-spar lifting surface of the present invention includes an axial rod fitting configured to connect an axial rod and a multi-spar torsional box, the axial rod fitting comprising:

[0026] - A longitudinal profile, including an L-shaped cross-section, comprising two wings, one wing abutting a portion of a surface of the open unit, and the other wing abutting a portion of a rear spar of the open unit, such that the longitudinal profile is positioned along the longitudinal direction of the rear spar at a corner with one of the surfaces.

[0027] - Lug, which is connected at one end to a longitudinal profile and at the other end to an axial rod, the lug defining a plane including the longitudinal axis of the axial rod.

[0028] Therefore, the load of the axial member is correctly transferred to the fixed structure. The load is first received by the lugs aligned with the longitudinal axis of the axial member, and then transferred to the flanges of the longitudinal profiles resting on the cover and the rear wing beam.

[0029] Furthermore, the multi-spar structure includes corner reinforcements for the spars. This means that all spar and skin corners are hard points, eliminating the need for any type of fittings. These corner reinforcements are thick enough to withstand lateral inertial loads.

[0030] Therefore, in the multi-wing lift surface that is to be protected, both components of the load transmitted by the axial rod are well received.

[0031] The advantages of this invention are as follows:

[0032] - Weight reduction.

[0033] - Cost reduction.

[0034] - The number of parts has been reduced.

[0035] - Assembly operations and tools are reduced.

[0036] -Simplified design.

[0037] Another object of the present invention is an aircraft including the lifting structure according to the above description. Attached Figure Description

[0038] To complete the description and to better understand the invention, a set of accompanying drawings is provided. These drawings form an integral part of the specification and illustrate preferred embodiments of the invention. These drawings include the following figures.

[0039] Figure 1 An exploded perspective view of the prior art lifting surface, anti-torsion box, and movable control surface is shown.

[0040] Figure 2 A plan view of an axial rod in the prior art is shown, which is connected to the rear wing beam of the anti-torsion box and to the articulated arm of the movable control surface.

[0041] Figure 3A A cross-sectional view of the lifting surface of a multi-spar beam according to a first embodiment of the present invention is shown. Figure 3B A detailed view of the multi-wing torsion box with multiple wing-spar lifting surfaces is shown.

[0042] Figure 4 A perspective view of a first embodiment of the axial rod fitting of the multi-spar lift surface of the present invention is shown.

[0043] Figure 5 It shows that according to Figure 4 The front view of the rear wing beam, lower cover, and axial rod fitting of the first embodiment shown.

[0044] Figure 6 It shows the location of the built-in position. Figure 4 and Figure 5 The side view of the first embodiment of the axial rod fitting shown.

[0045] Figure 7 A perspective view of a second embodiment of the axial rod fitting for the multi-spar lift surface of the present invention is shown.

[0046] Figure 8 It shows that according to Figure 7 The rear wing beam, lower cover, and axial rod fitting of the second embodiment shown are front views.

[0047] Figure 9 A plan view of an aircraft having a multi-spar lifting surface according to the present invention is shown. Detailed Implementation

[0048] Figure 1 The prior art lifting surface 8 is disclosed, which has an anti-torsion box 2, a movable operating surface, a hinge element 6, and an axial rod 7.

[0049] As described above, a conventional anti-torsion box 2 includes ribs, wing beams, stringers, and a cover.

[0050] The movable control surface is equipped with upper and lower arms 6.2 and 6.3 for receiving loads from the movable control surface. The movable control surface is positioned adjacent to the rear end of the anti-torsion box 2 and includes:

[0051] -Modible component 1,

[0052] - Hinged element 6, which includes a hinge connector 6.1 connected to the movable element 1, and an upper arm 6.2 and a lower arm 6.3. Each arm 6.2 and 6.3 includes a first end positioned in the hinge connector 6.1 and a second end positioned in the rear wing beam 5 along the transverse direction of the rear wing beam 5. The second end of the upper arm 6.2 is positioned in the corner formed by the upper cover 4 and the rear wing beam 5, and the second end of the lower arm 6.3 is positioned in the corner formed by the lower cover 3 and the rear wing beam 5. The plane including the upper arm and the lower arm 6.2 and 6.3 is substantially perpendicular to the longitudinal direction of the rear wing beam 5.

[0053] - Axial rod 7, which includes a first end located in the hinged connector 6.1 and a second end located in the rear wing beam 5 longitudinally away from the upper and lower arms 6.2, 6.3.

[0054] In the illustrated embodiment, the hinge element 6 further includes a rear arm 6.4 connected to the first arm 6.2 and the second arm 6.3, and abutting against the rear spar 5 at a first position along the longitudinal direction of the rear spar 5.

[0055] As previously mentioned, the axial rod 7 is a fixed structure that extends from the movable control surface to the anti-torsion box 2 (specifically, a diagonal bar that extends to the rear wing beam 5).

[0056] Figure 2 The axial rod 7 connected to the conventional torsion box 2 is shown. The "Y" component of the load transmitted by the axial rod 7 is received by the rear spar 2.2, and the "X" component is received by the rib 2.1, as shown. Figure 2 As depicted, as described above, the counterbalancing fitting 2.3 must be installed inside the anti-torsion box 2 in order to properly introduce the load into the structure.

[0057] Figure 3A The multi-spar lifting surface 30 according to the invention is depicted, which includes a multi-spar anti-torsion box 32, a movable control surface (as defined, mounted in a multi-unit structure) and an axial rod fitting 40.

[0058] The multi-wing torsion box 32 structure is made of composite materials and includes the following structural elements:

[0059] - Upper surface 3,

[0060] - Lower surface 4,

[0061] - Multiple wing spars, including rear wing spars 5.

[0062] - Open unit 21, which opens toward the rear end of the torsion box 32, and is formed by a portion of the upper surface 3, a portion of the lower surface 24, and the rear wing spar 5, and

[0063] - Enclosed unit 22, which is adjacent to open unit 21, and is formed by upper surface 23, lower surface 24, rear spar 5 and another spar 51 adjacent to rear spar 5.

[0064] In addition, such as Figure 3B As shown, according to the present invention, the multi-wing beam anti-torsion box 32 further includes a corner reinforcement 25 formed by increasing the thickness of at least the following portions:

[0065] - The corner of open unit 21 formed by the upper and lower surfaces 23, 24 and the rear wing spar 5, and

[0066] - The corner of the enclosed unit 22 formed by the upper and lower surfaces 23 and 24 and the rear wing beam 5.

[0067] These reinforced corners serve as hard points, eliminating the need for any offset fittings.

[0068] The movable control surface of the present invention also includes a movable element 1, a hinge element 6, and an axial rod 7. For the hinge element 6, since a multi-unit structure is used as an anti-torsion box, the second ends of the upper arm and lower arm 6.2, 6.3 are now positioned in the corner of the open unit 21, but the element and its position are the same as in the prior art.

[0069] like Figure 3A As shown, the hinge element 6 of the movable control surface preferably defines a plane including upper and lower arms 6.2, 6.3, which is generally perpendicular to the longitudinal direction of the rear spar 5.

[0070] Figure 4 and Figure 7 Two embodiments of the axial rod fitting 40 of the present invention are disclosed.

[0071] Axial rod fitting 40 includes:

[0072] - Longitudinal profile 10, including an L-shaped cross-section. Longitudinal profile 10 includes two wings 11 and 12. One wing 11 is configured to abut a portion of one of the surfaces 23 and 24 of the open unit 21 of the multi-spar torsion box 32. The other wing 12 is configured to abut a portion of the rear spar 5 of the open unit 21 of the multi-spar torsion box 32. Therefore, longitudinal profile 10 is configured to be positioned at the corner of the rear spar 5 and surfaces 23 and 24. Longitudinal profile 10 is configured to be positioned such that its longitudinal axis is parallel to the longitudinal axis of the rear spar 5.

[0073] - Lug 20, which is connected at one end to the longitudinal profile 10 and includes means for connecting at its other end to the axial rod 7. Lug 20 includes a plane configured to include the longitudinal axis of the axial rod 7 in its mounting position. In the illustrated embodiment, lug 20 is planar and includes a hole for connection with the axial rod 7.

[0074] The axial rod 7 is positioned obliquely relative to the rear spar 5, and as described above, the axial rod fitting 40 is positioned at the corner of the open unit 21 between the rear spar 5 and surfaces 23, 24. Therefore, the longitudinal axis of the axial rod 7 forms an angle of approximately 45° with the longitudinal direction of the plane of the wing 12 configured to be positioned against the rear spar 5.

[0075] The axial rod fitting 40 can be positioned at the corner between the lower surface 24 and the rear wing beam 5, or at the corner between the upper surface 23 and the rear wing beam 5.

[0076] like Figure 3A As shown, if positioned at the lower corner, the axial rod 7 forms an angle of 60° to 70° with the longitudinal direction of the plane of the wing 12, which is configured to be positioned against the rear wing beam 5.

[0077] The lug 20 includes a plane intersecting with the wings 11 and 12 of the longitudinal profile 10. Figures 4 to 7 In the embodiment shown, the intersection of the plane of the lug 20 with one of the wings 11 and 12 is perpendicular to the longitudinal direction of the longitudinal profile 10.

[0078] The above configuration allows sufficient space to directly mount the axial rod fitting 40 to the structure using solid rivets or hi-lok rivets, and sufficient space to use the standard axial rod 7 and connect it using the same fasteners as in the prior art.

[0079] More specifically, the wing 12, which intersects the longitudinal direction of the longitudinal profile 10 at a right angle, is configured to abut against the rear wing spar 5.

[0080] Figure 6 The plane of lug 20 and the plane of wing 12 resting at 45° on the rear wing spars 5 are shown.

[0081] Figure 7 and Figure 8 A second embodiment is disclosed, wherein the lug 20 includes a plane that intersects the L-shaped profile along the longitudinal profile 10 between the two wings 11, 12.

[0082] In these Figures 7 to 8 In the embodiment shown, the plane of the lug 20 forms a 60° angle with the plane of the wing portion 12 configured to abut against the rear spar 5.

[0083] This solution offers better load distribution, especially a constant distribution along the corner of the lower surface 4 and the rear wing beam 5, but it requires more space for the installation of the axial rod 7.

[0084] In the illustrated embodiment, the lug 20 is configured to connect to the lower surface 24 of the multi-spar anti-torsion box 32.

[0085] In the case of elevator and horizontal stabilizer (HTP), the lower part of the axial rod fitting 40 at the corner between the lower surface 24 and the rear spar 5 is divided by the axial rod 7 at a ratio of approximately 30° to 60°, as shown below. Figure 3A As shown in the image.

[0086] The axial rod fitting 40 can also be connected to the upper surface 23, i.e., positioned in the upper corner of the rear wing spar 5. In the case of HTP, due to the typical difference between the distances from the elevator hinge line to the upper and lower surfaces 23 and 24, the shorter distance to the upper surface 23 and the smaller angle complicate installation and reduce load transfer efficiency.

Claims

1. A multi-wing spars lifting surface (30), comprising: - Multi-spar torsion box (32), the multi-spar torsion box being made of composite material and including an upper surface (23) and a lower surface (24) and a plurality of spars forming a multi-unit structure between the upper surface (23) and the lower surface (24), the plurality of spars including a rear spar (5), the rear spar defining: - An open unit (21) is open toward the rear end of the anti-torsion box (32) and is formed by a portion of the upper surface (23), a portion of the lower surface (24), and the rear wing spar (5). - A closed unit (22), which is adjacent to the open unit (21) and is formed by the upper surface (23), the lower surface (24), the rear wing spar (5) and another wing spar (51) adjacent to the rear wing spar (5). - Movable control surfaces, including: -Modible element (1) - A hinge element (6), the hinge element comprising a hinge connector (6.1) connected to the movable element (1), and an upper arm (6.2) and a lower arm (6.3), the upper arm (6.2) and the lower arm (6.3) each comprising a first end positioned in the hinge connector (6.1) and a second end positioned in the rear wing beam (5) along the lateral direction of the rear wing beam (5), the second end of the upper arm (6.2) being positioned in the corner of the open unit (21) formed by the upper surface (23) and the rear wing beam (5), and the second end of the lower arm (6.3) being positioned in the corner of the open unit (21) formed by the lower surface (24) and the rear wing beam (5). - An axial rod (7), the axial rod comprising a first end positioned in the hinged connector (6.1) and a second end positioned in the rear wing beam (5) longitudinally away from the upper arm (6.2) and the second end of the lower arm (6.3), The multi-wing beam anti-torsional box (32) is characterized in that it further comprises: -Corner reinforcement (25) formed by increasing the thickness of at least the following parts: - The corner of the open unit (21) formed by the upper surface (23), the lower surface (24), and the rear wing spar (5), and - The corner of the enclosed unit (22) formed by the upper surface (23), the lower surface (24), and the rear wing beam (5), Furthermore, the multi-spar lifting surface (30) is characterized in that it further comprises: - An axial rod fitting (40) is configured to connect the axial rod (7) to the multi-wing torsion box (32), the axial rod fitting (40) comprising: - A longitudinal profile (10) comprising an L-shaped cross section, the longitudinal profile (10) comprising two wings (11, 12), one of the wings abutting a portion of one of the surfaces of the upper surface (23) and the lower surface (24) of the open unit (21), and the other wing abutting a portion of the rear spar (5) of the open unit (21), such that the longitudinal profile (10) is positioned along the longitudinal direction of the rear spar (5) at a corner with one of the surfaces of the upper surface (23) and the lower surface (24), and - Lug (20), which is connected at one end to the longitudinal profile (10) and at the other end to the axial rod (7), the lug (20) defining a plane including the longitudinal axis of the axial rod (7).

2. The multi-wing spar lifting surface (30) according to claim 1, wherein, The axial rod fitting (40) is positioned at the corner of the lower surface (24) of the open unit (21) and the rear wing beam (5), or at the corner of the upper surface (23) and the rear wing beam (5).

3. The multi-wing spar lifting surface (30) according to claim 2, wherein, The longitudinal axis of the axial rod (7) forms an angle of 60° to 70° with the transverse direction of the plane of the wing portion positioned against the rear wing beam (5).

4. The multi-spar lifting surface (30) according to any one of claims 1 to 3, wherein, The longitudinal axis of the axial rod (7) forms a 45° angle with the longitudinal direction of the plane of the wing portion positioned against the rear wing beam (5).

5. The multi-spar lifting surface (30) according to any one of claims 1 to 3, wherein, The lug (20) includes a plane that intersects with the wings (11, 12) of the longitudinal profile (10).

6. The multi-wing spar lifting surface (30) according to claim 5, wherein, The intersection of the plane of the lug (20) with one of the wings (11, 12) is perpendicular to the longitudinal direction of the longitudinal profile (10).

7. The multi-wing spar lifting surface (30) according to claim 6, wherein, The wing that intersects the longitudinal direction of the longitudinal profile (10) at a right angle is the wing that abuts against the rear wing beam (5).

8. The multi-wing spar lifting surface (30) according to claim 5, wherein, The lug (20) includes a plane that intersects the longitudinal profile (10) along the portion of the longitudinal profile (10) between the two wings (11, 12).

9. The multi-spar lifting surface (30) according to any one of claims 1 to 3, wherein, The hinge element (6) further includes a rear arm (6.4) connected to the upper arm (6.2) and the lower arm (6.3) and abutting against the rear wing spar (5).

10. An aircraft, characterized in that, The aircraft includes a multi-spar lifting surface as described in any one of claims 1 to 9.

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