Trailing edge for a compound lifting surface

Abstract

The present invention relates to a trailing edge for a compound lifting surface, the trailing edge comprising: a spar; an upper panel and a lower panel including a free edge; a seal; and an elongate profile which is located on the panel along the span direction of the trailing edge, and the elongate profile includes a web and a first flange portion and a second flange portion, the web extends along the span direction of the trailing edge, the first flange portion and the second flange portion extend relative to each other at different heights and have a transition region therebetween, the first flange portion is configured to hold at least a part of the seal thereunder, and the second flange portion is configured to contact the panel, the first flange portion fixes the seal to the panel, and the second flange portion fixes the elongate profile to the panel.

Description

Field of the Invention

[0001] The present invention relates to a trailing edge of a fin or wing structure. More specifically, the trailing edge is a trailing edge that includes a unit concept fully integrated in a multi-beam torsion box. Background Art

[0002] An aircraft lifting surface includes a torsion box as its main support structure, to which a leading edge and a trailing edge are attached; and further includes control surfaces attached to the trailing edge or the leading edge, such as flaps, rudders or elevators.

[0003] The leading edge is attached to the front beam of the torsion box. The trailing edge is attached to the rear beam of the torsion box, and the trailing edge allows the installation and movement of control surfaces to complete the aircraft lifting surface.

[0004] A known structural design of the torsion box is a multi-beam torsion box. The multi-beam torsion box includes a plurality of beams extending in the span direction. The beams further include at least flanges and webs, thereby creating closed cells.

[0005] The torsion box includes an upper skin panel and a lower skin panel, which are elements that enclose the entire torsion box in the upper and lower parts.

[0006] The trailing edge is the free edge behind the last beam of the torsion box, and the trailing edge includes an upper skin panel and a lower skin panel, a removable sealing profile in interface connection with the control surface, and a mounting portion. Due to the installation of systems, equipment and control surfaces, the trailing edge includes a removable channel panel. The sealing profile is usually installed by a removable metal profile.

[0007] The channel panel must meet certain requirements:

[0008] · Aerodynamic requirements, such as low air resistance.

[0009] · Resistance to aerodynamic forces.

[0010] · Strength and stiffness requirements to avoid buckling and significant deformation.

[0011] Conventional trailing edge panels (i.e., panels of non-integrated trailing edges) are strengthened by using sandwich structures.

[0012] An integrated structure is a structure in which different structural elements subjected to different stresses (shear stress, normal stress, etc.) are manufactured in one piece or at one time, or starting from a single piece of material.

[0013] The trailing edge of a multi-beam integrated lifting surface is manufactured by a one-shot feeding method, so the trailing edge is integral, and the channel panel cannot be strengthened by a sandwich structure.

[0014] In the case of the overall panel, it is necessary to increase the thickness to ensure the appropriate stiffness of the panel. However, in thin and slender components (such as the trailing edge panel), the increase in thickness must be very significant.

[0015] The multi-spar trailing edge analysis shows that the maximum deformation always occurs at the free edge of the trailing edge. And the buckling shape of the lower panel indicates that the onset of buckling also occurs in the free edge of the panel. The analysis shows that the area with the maximum load on the trailing edge panel is just adjacent to the free edge.

[0016] In addition, it is also known that the multi-spar element concept is based on spars made of C-shaped composite forms, and the flanges of the C-shaped composite spars extend in the skin chordwise direction in the cross-section of the trailing edge.

[0017] Due to the multi-spar design guidelines, only two types of fiber plies are allowed in the last element of the trailing edge. Other types of fiber plies are disabled due to the thermoforming process and the molding process, because all layers must start on the spar, otherwise they will move during the manufacturing process.

[0018] Specifically, a C-shaped or L-shaped form can be adopted. As a result, in this type of trailing edge reinforcement, some parts of the element must be enlarged in size, and as a result, the entire trailing edge is enlarged in size, thus increasing the material, labor costs, and weight. Summary of the Invention

[0019] An object of the present invention is a trailing edge for a composite lifting surface. The trailing edge is a trailing edge that at least includes a spar extending in the spanwise direction of the trailing edge, and an upper panel and a lower panel extending from the spar (or composed of separate panels extending from the spar, or composed of the same panel forming an integrated trailing edge).

[0020] The upper panel and the lower panel include four edges. The upper panel and the lower panel include free edges in the edges opposite to the edges adjacent to the spar in the chordwise direction of the trailing edge. The free edges of the panels are created due to the openings configured for attaching the trailing edge of the control surface.

[0021] The trailing edge further includes a seal that is installed to seal the movable control surface against the panel, thereby closing the gap between the panel and the movable control surface.

[0022] According to the present invention, the trailing edge further includes an elongate profile connected to the upper panel and / or the lower panel.

[0023] The elongate profile is interpreted in the present invention as a long and thin profile. The profile refers to a hot-rolled / extruded / molded / forged formed part to be cut into sheets of material (such as laminated plastics, aluminum alloys, or steel plates).

[0024] The elongate profile follows the spanwise direction of the trailing edge, is located between the spar and the free edge of the upper panel and / or the lower panel, and is closer to the free edge than the spar and is located on the upper panel and / or the lower panel.

[0025] The profile includes a web, and a first flange portion and a second flange portion, with a transition region therebetween. The web extends in a direction perpendicular to the plane defined by the panel along the spanwise direction of the trailing edge. The first flange portion and the second flange portion extend relative to each other at different heights. The first flange portion is configured to hold at least a part of the seal thereunder, and the second flange portion is configured to contact the panel. The first flange portion secures the seal to the panel, and the second flange portion secures the elongate profile to the panel.

[0026] Accordingly, an object of the present invention is to stiffen the trailing edge integral panel using the same profile as that used for fixing the aerodynamic seal. To provide a multi-functional profile for the integral panel (i.e., a panel with a multi-spar structure manufactured by a one-shot feeding method), rather than increasing the thickness of the panel as known in the prior art in the field.

[0027] Accordingly, the present invention allows the panel to be stiffened without increasing the panel thickness and without the need to increase the sandwich structure. Additionally, the present invention provides a structure that allows the seal to be replaced without having to remove the profile.

[0028] All panels are always supported by trailing edge ribs and spars or hinges on three of their four edges and have one free edge. As previously mentioned, with an increase in thickness, the entire panel is strengthened at the same level and is also oversized in areas with lower loads.

[0029] Additionally, the elongate profile can fix other components, such as seals.

[0030] The trailing edge of the present invention includes the following advantages:

[0031] · Allows for the manufacture of a trailing edge with a multi-spar structure in one go and simultaneously provides sufficient stiffness for the trailing edge panel.

[0032] · Involves fewer components.

[0033] · The possibility of using the profile as an electrical bonding strip.

[0034] · Reduced weight.

[0035] · Reduced cost.

[0036] The moment of inertia of the rectangular portion (first flange portion and second flange portion) of the profile increases with its height. Also, the moment of inertia of the rectangular portion of the profile is more effective when the distance between the web and the free edge of the panel of the profile decreases.

[0037] As previously mentioned, the object of the present invention is that the trailing edge can be integrated.

[0038] A composite lift surface is also an object of the present invention, which composite lift surface includes a leading edge, a torsion box, and a trailing edge attached to the torsion box and as described above.

[0039] The ultimate object of the present invention is an aircraft that includes a composite lift surface as described above. Description of the Drawings

[0040] To complete the description and to better understand the present invention, a set of drawings is provided. The said drawings form an integral part of the description and show the preferred embodiments of the present invention. These drawings include the following figures.

[0041] Figure 1 A schematic cross-sectional view of an aircraft lift surface having a trailing edge according to the present invention is shown.

[0042] Figure 2 A detailed view of a trailing edge according to an embodiment of the present invention is shown.

[0043] Figure 3 A detailed view of a trailing edge according to another embodiment of the present invention is shown.

[0044] Figure 4 An aircraft having a lift surface with a trailing edge according to the present invention is shown. Detailed Description of the Invention

[0045] Figure 1 An aircraft lift surface 1 is disclosed, including a torsion box 3 as its main support structure, wherein a leading edge 4 and a trailing edge 2 are attached to the torsion box 3. As in this case, control surfaces 8, such as flaps, rudders or elevators, are also attached to the trailing edge 2.

[0046] Figure 1 The trailing edge 2 is also disclosed in the shown cross-section, which trailing edge includes a spar 22 positioned in the spanwise direction of the trailing edge 2 and substantially parallel to the rear spar 20 of the torsion box. Figure 1 Upper and lower panels 9 are also disclosed, which upper and lower panels extend towards the trailing edge spar 22 and include free edges 23 at the edges opposite to the edges of the panels 9 closer to the trailing edge spar 22.

[0047] As Figure 1As shown, the trailing edge 2 further includes a seal 5 configured to seal the control surface 8 against the panel 9. The seal 5 is connected to the upper panel and the lower panel 9 near the free ends 23 of the upper and lower panels by means of a profiled section 7.

[0048] Figure 2 and Figure 3 Two different embodiments of the profiled section 7 of the present invention are disclosed. The profiled section 7 is mounted on the upper panel and / or the lower panel 9 along the span direction of the trailing edge 2, between the trailing edge spar 22 and the free edge 23 of the panel. The profiled section 7 is positioned closer to the free edge 23 compared to the trailing edge spar 22.

[0049] The profiled section 7 includes a web 71, a first flange portion and a second flange portion 72, 73, and a transition region 74 between the first flange portion and the second flange portion. The web 71 extends perpendicular to the plane defined by the panel 9 along the span direction of the trailing edge 2. The first flange portion and the second flange portion 72, 73 extend at different heights relative to each other, relative to the web 71, and relative to the plane defined by the panel 9.

[0050] The first flange portion 72 is configured to hold at least a part of the seal 5 thereunder, and the second flange portion 73 is configured to contact the panel 9. The first flange portion 72 fixes the seal 5 to the panel 9, and the second flange portion 73 fixes the profiled section 7 to the panel 9.

[0051] The profiled section 7 is positioned between the free edge 23 of the panel and a position 1 / 3 of the chord length of the panel 9 away from the free edge 23 of the panel. Thus, the profiled section is positioned such that the web 71 is located in the region of the greatest load.

[0052] In the illustrated embodiment, the chord length (the shortest dimension) of the profiled section 7 is between 5% and 15% of the chord length of the panel 9.

[0053] In addition, in the illustrated embodiment, the height of the web 71 is approximately 5% of the chord length of the panel 9, which is sufficient to stiffen the panel and thus avoid buckling.

[0054] Figure 2 A first embodiment of the profiled section 7 is shown, in which the first flange portion and the second flange portion 72, 73 extend continuously along the chord direction of the trailing edge 2. In this case, the web 71 is located at one end of the profiled section 7 close to the trailing edge spar 22.

[0055] Figure 3 A second embodiment of the profiled section 7 is shown, in which the web 71 is located between the first flange portion and the second flange portion 72, 73.

[0056] Figure 2 and Figure 3 shows a transition region 74 that includes a ramp, although other configurations may also be used.

[0057] Preferably, the trailing edge 2 further includes a removable fastener 6 that secures the first flange portion 72 and the seal 5 to the panel 9. In this way, the seal can be replaced when needed.

[0058] In addition, the trailing edge 2 may further include a rivet 40 that secures the second flange portion 73 to the panel 9. Preferably, solid, hi-lock, or hi-lite rivets will be used.

[0059] As an advantage, using different types of fasteners to secure the elongated profile avoids disassembling the entire profile when the seal must be replaced. This saves time and reduces costs.

[0060] As previously mentioned, the trailing edge 2 includes a seal 5 that is configured to seal the control surface 8 against the panel 9. The seal 5 is connected to the upper and / or lower panel 9 of the trailing edge 2 by the first flange portion 72 of the elongated profile 7. Thus, the elongated profile 7 also serves to help secure the seal 5 to the panel 9.

[0061] In an embodiment, the seal 5 is made of rubber.

[0062] According to another preferred embodiment, the seal 5 includes an elongated extension 51 that extends parallel to the panel 9. Preferably, the seal 5 has a "P" - shaped or "I" - shaped cross - sectional shape.

[0063] When the distance between the web 71 and the free edge 23 of the panel 9 decreases, the stiffness of the elongated profile 7 is more effective. Thus, Figure 3 the embodiment of

[0064] In an embodiment, the elongated profile 7 extends along the entire span of the panel 9.

[0065] The elongated profile 7 is preferably metallic.

[0066] A composite lift surface 1 is also an object of the present invention, the composite lift surface including a leading edge 4, a torsion box 3, and a trailing edge 2 attached to the torsion box 3, wherein the composite lift surface 1 includes the trailing edge 2 as described above.

[0067] Figure 4 An aircraft including the composite lift surface 1 according to the above is disclosed.

Claims

1. A trailing edge (2) for a compound lifting surface (1), the trailing edge comprising: A spar (22) extending in the spanwise direction of the trailing edge (2), An upper panel and a lower panel (9) extending from the spar (22) and including a free edge (23) opposite the spar (22), A seal (5) mounted to seal a control surface (8) against the upper panel and the lower panel (9), and An elongate profile (7) following the spanwise direction of the trailing edge (2), between the spar (22) and the free edge (23) of the upper panel and / or the lower panel, and located on the upper panel and / or the lower panel (9) closer to the free edge (23) than the spar (22), the elongate profile (7) comprising: A web (71) extending in the spanwise direction of the trailing edge (2) and perpendicular to the plane defined by the upper panel and the lower panel (9), and A first flange portion and a second flange portion (72, 73) extending relative to each other at different heights and having a transition region (74) therebetween, the first flange portion (72) being configured to hold at least a part of the seal (5) thereunder, and the second flange portion (73) being configured to contact the upper panel and the lower panel (9), the first flange portion (72) fixing the seal (5) to the upper panel and the lower panel (9), and the second flange portion (73) fixing the elongate profile (7) to the upper panel and the lower panel (9).

2. The trailing edge (2) for a compound lifting surface (1) according to claim 1, wherein, The elongate profile (7) is positioned between the free edge (23) of the upper panel and the lower panel and a position at a length of 1 / 3 of the chordwise length of the upper panel and the lower panel (9) away from the free edge (23) of the upper panel and the lower panel.

3. The trailing edge (2) for a compound lifting surface (1) according to claim 1 or 2, wherein, The chordwise length of the elongate profile (7) is between 5% and 15% of the chordwise length of the upper panel and the lower panel (9).

4. The trailing edge (2) for a compound lifting surface (1) according to claim 1 or 2, wherein, The height of the web (71) is approximately 5% of the chordwise length of the upper panel and the lower panel (9).

5. The trailing edge (2) for a compound lifting surface (1) according to claim 1 or 2, wherein, The first flange portion and the second flange portion (72, 73) extend continuously in the chordwise direction of the trailing edge (2).

6. The trailing edge (2) for a compound lifting surface (1) according to claim 5, wherein, The web (71) is located at an end of the elongate profile (7) closer to the spar (22).

7. The trailing edge (2) for a compound lifting surface (1) according to claim 1 or 2, wherein, The web (71) is located between the first flange portion and the second flange portion (72, 73).

8. The trailing edge (2) for a compound lifting surface (1) according to claim 1 or 2, the trailing edge further comprising removable fasteners (6) for fixing the first flange portion (72) and the seal (5) to the upper panel and the lower panel (9).

9. The trailing edge (2) for a compound lifting surface (1) according to claim 1 or 2, the trailing edge further comprising rivets (40) for fixing the second flange portion (73) to the upper panel and the lower panel (9).

10. The trailing edge (2) for a compound lifting surface (1) according to claim 1 or 2, wherein, The seal (5) includes an elongate extension (51) extending parallel to the upper panel and the lower panel (9).

11. The trailing edge (2) for a compound lifting surface (1) according to claim 1 or 2, wherein, The seal (5) has a "P" - shaped or "I" - shaped cross - sectional shape.

12. The trailing edge (2) for a compound lifting surface (1) according to claim 1 or 2, wherein, The elongated profile (7) extends along the entire span of the upper panel and the lower panel (9).

13. A composite lifting surface (1) comprising a leading edge (4), a torsion box (3), and a trailing edge (2) attached to the torsion box (3), wherein the composite lifting surface (1) is characterized in that the composite lifting surface comprises a trailing edge (2) according to any one of claims 1 to 12.

14. An aircraft, characterized in that, The aircraft comprises a composite lifting surface (1) according to claim 13.

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