TRAILING EDGE FOR A COMPOSITE MULTISPAR INTEGRATED LIFTING SURFACE AND METHOD FOR MANUFACTURING SAID TRAILING EDGE

Abstract

A trailing edge for a composite multispar integrated lifting surface includes a first C-shape composite form that includes a web and two flanges. The web forming a portion of the rear spar of a torsion box. The two flanges extending along a skin chordwise direction. A second C-shape composite form includes a web and two flanges. The web forms an auxiliary spar. The flanges extend along the skin chordwise direction. The first C-shape composite form and the second C-shape composite form forming a first auxiliary cell and a second cell. The first auxiliary cell is delimited by the first C-shape composite form and the second C-shape composite form. The second cell is an open cell delimited by the second C-shape composite form.

Claims

1. A trailing edge for a composite multispar integrated lifting surface, the lifting surface comprising a leading edge, a multispar torsion box, a trailing edge attached to the torsion box through a rear spar of the torsion box and upper and lower skins, the trailing edge comprising: a first C-shape composite form that comprises a web and two flanges, the web configured to form a portion of the rear spar of the torsion box and the two flanges extending along a skin chordwise direction of the trailing edge, a second C-shape composite form comprising a web and two flanges, the web forming an auxiliary spar of the trailing edge and the flanges extending along the skin chordwise direction of the trailing edge, the first C-shape composite form and the second C-shape composite form are configured such that a first auxiliary cell and a second cell are formed, the first auxiliary cell being delimited by the web and the two flanges of the first C-shape composite form and by the web of the second C-shape composite form, the second cell being an open cell delimited by the web and the two flanges of the second C-shape composite form.

2. The trailing edge for a composite multispar integrated lifting surface, according to claim 1, wherein the two flanges of the first C-shape composite form comprise a further bent part parallel to the web of the first C-shape composite form, the bent parts being applied against the web of the second C-shape composite form for forming the auxiliary spar together with the web.

3. The trailing edge for a composite multispar integrated lifting surface, according to claim 2, wherein the bent parts of the first C-shape composite form extend along a portion of the web of the second C-shape composite form.

4. A composite multispar integrated lifting surface, comprising: a leading edge, a multispar torsion box, and a trailing edge, formed according to claim 1, attached to the torsion box through a rear spar of the torsion box and upper and lower skins.

5. An aircraft comprising a composite multispar integrated lifting surface according to claim 4.

6. A method for manufacturing a trailing edge for a composite multispar integrated lifting surface comprising a leading edge, a multispar torsion box, a trailing edge attached to the torsion box through a rear spar of the torsion box and upper and lower skins, comprising the following steps: stacking a first and a second composite laminate carried out by a manual or automatic process, bending the first composite laminate to form a first C-shape composite form that comprises a web and two flanges, bending the second composite laminate to form a second C-shape composite form comprising a web and two flanges, joining the first C-shape composite form to the second C-shape composite form such that: the two flanges of the first C-shape composite form extend along a skin chordwise direction of the trailing edge and the two flanges of the second C-shape composite form extend along the skin chordwise direction of the trailing edge, the web of the second C-shape composite form forms an auxiliary spar of the trailing edge, and a first auxiliary cell and a second cell are formed, the first auxiliary cell being delimited by the web and the two flanges of the first C-shape composite form and by the web of the second C-shape composite form and the second cell being an open cell delimited by the web and the flanges of the second C-shape composite form, the web of the first C-shaped composite form being configured to be applied against the rear spar of the torsion box such that the web is configured to form a portion of the rear spar of the torsion box, and co-curing the trailing edge and the torsion box in one shot.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0061] To complete the description and in order to provide for a better understanding of the invention, a set of drawings is provided. The drawings form an integral part of the description and illustrate preferred embodiments of the invention. The drawings comprise the following figures.

[0062] FIG. 1 shows a schematic perspective view of a torsion box known in the state of the art.

[0063] FIG. 2 shows a schematic view of a cross-section of a double C-shape integrated multispar torsion box known in the state of the art.

[0064] FIG. 3 shows an enlarged view of two double C-shape forms according to the embodiment of FIG. 2.

[0065] FIG. 4 shows a schematic view of a cross-section of a trailing edge and a portion of a torsion box according to an embodiment of the invention.

[0066] FIG. 5 shows an enlarged view of the embodiment of the trailing edge according to FIG. 4.

[0067] FIG. 6 shows a cross-section perspective view of an embodiment of a lifting surface according to the invention.

[0068] FIG. 7 shows a cross-section of an embodiment of a trailing edge according to the invention and a rib attached to the auxiliary spar.

[0069] FIG. 8 shows an aircraft according to the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0070] FIGS. 1, 2 and 3 show an integrated torsion box according to the state of the art.

[0071] FIG. 1 shows a perspective view of a torsion box (3) comprising spars (40) running along the spanwise direction of the torsion box (3). An upper skin (41) is also shown.

[0072] FIG. 2 shows a double C-shaped structure comprising C-shaped composite forms (43) located facing each other such that cells (44) are formed delimited by the web and flanges of every two C-shaped composite forms (43).

[0073] FIG. 3 shows a detailed view of FIG. 2 showing a spar (40) formed by locating together two webs of two C-shaped composite forms (43).

[0074] FIG. 4 shows a multispar portion of a torsion box (3) according to the state of the art shown in FIGS. 2 and 3 and a trailing edge (2) according to an embodiment of the invention.

[0075] FIGS. 5 and 6 show a trailing edge (2) that comprises:

[0076] A first C-shape composite form (10) that comprises a web (11) and two flanges (12), the web (11) forming part of the rear spar (20) of the torsion box (3). The other part of the rear spar (20) of the torsion box (3) is formed by the web (45) of the adjacent C-shaped composite form (43) of the torsion box (3). The first C-shaped composite form (10) also comprises two flanges (12), both flanges (12) extend along the skin (21) chordwise direction of the trailing edge (2), specifically along the upper and lower skins (21) towards the rear end of the trailing edge (2).

[0077] A second C-shape composite form (15) also comprising a web (16) and two flanges (17). The web (16) forms the auxiliary spar (22) and the flanges (17) extends along the skin (21) chordwise direction of the trailing edge (2) towards its rear end.

[0078] Therefore, a first auxiliary cell (30) and a second cell (31) are formed. The first auxiliary cell (30) is delimited by part of the rear spar (20), specifically by the web (11) of the first C-shape composite form (10) and by the two flanges (17) of the first C-shape composite form (10) and by the auxiliary spar (22) which is formed by the web (16) of the second C-shape composite form (15). The second cell (31) is the open cell delimited by the auxiliary spar (22), i.e., the web (16) of the second C-shape composite form (15) and the two flanges (17) of the second C-shape composite form (15).

[0079] More particularly, in the shown embodiment, the flanges (12) of the first C-shape composite form (10) comprise a bent part (18) which is parallel to the web (11) of the first C-shape composite form (10). As the flanges (12) extend along the skin (21) chordwise direction, each bent part (18) extends towards the other bent part (18). The flanges (12) of the first C-shape composite form (10) extend along the skin (21) chordwise direction up to the auxiliary spar (22) and then along the auxiliary spar (22) surface, i.e., along the web (16) of the second C-shape composite form (15).

[0080] Thus, in the shown embodiment, the auxiliary spar (22) is formed by the web (16) of the second C-shape composite form (15) and the further bent parts (18) of the first C-shape composite form (10).

[0081] The bent part (18) is applied to the web (16) of the second C-shape form (15) or, what is the same, is attached to the web (16) of the second C-shape form (15). In that way, the auxiliary spar (22) is stiffened by the bent parts (18) of the first C-shape form (10).

[0082] In FIG. 5 is shown that the bent part (18) of the first C-shape form (10) extend along just a portion of the web (16) of the second C-shape form (15). Thus, the auxiliary spar (22) has the particularity to show two different thickness areas. Upper and lower areas of the auxiliary spar (22) comprises the bent part (18) of the first C-shape composite form (10) and the web (16) of the second C-shape composite form (15). The auxiliary spar (22) comprises a second area in the middle portion of the auxiliary spar (22) where only the web (16) of the second C-shape form (15) exists.

[0083] FIG. 7 discloses bearing ribs or hinge ribs (50) that may be attached to upper and lower flanges (17) to transmit loads coming from the control surfaces. As previously stated, this reduces the size of bearing ribs (50) that may be attached to the auxiliary spar (22) instead of to the rear spar (20) of the torsion box (3), improving its cost and weight.

[0084] The detailed steps of an embodiment of the method for manufacturing a multispar integrated trailing edge (1) of composite material will be described below, which process may be divided into the following steps:

[0085] In step 1, the, for instance, carbon fiber or fiberglass, layers are separately stacked in a planar manner, which layers form each element.

[0086] In step 2, the stack is bent. This bending can be carried out in different ways, preferably by means of applying a vacuum and temperature cycle molding the stack with the desired geometry by means of the suitable jig.

[0087] In step 3, the different elements are joined to form the integrated structure, according to FIGS. 4 to 6.

[0088] In step 4, the complete structure is cured by means of applying a pressure and temperature cycle, with the aid of the suitable jig system, which allows the suitable compaction of all the areas of the structure.

[0089] While at least one exemplary embodiment of the present invention(s) 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.