REINFORCED LEADING EDGE SECTION FOR AN AIRCRAFT

Abstract

A reinforced leading edge section for an aircraft, including an outer skin formed with an aerodynamic leading edge profile, an inner reinforcement arranged internally with respect to the outer skin along the span of the leading edge section, wherein the inner reinforcement includes a base with a C-shaped configuration joined to the outermost part of the outer skin, and a web having a free end and an opposite end joined to the base, the web extended in a direction transverse to the direction of the span of the leading edge section.

Claims

1. A reinforced leading edge section for an aircraft, comprising: an outer skin formed with an aerodynamic leading edge profile, and an inner reinforcement arranged internally with respect to the outer skin along a span of the leading edge section, wherein said inner reinforcement comprises a base with a C-shaped configuration joined to an outermost part of the outer skin, and a web having a free end and an opposite end joined to the base, the web extended in a direction transverse to a direction of the span of the leading edge section.

2. The reinforced leading edge section for an aircraft, according to claim 1, comprising at least one pair of secondary reinforcements attached to both ends of the base of the inner reinforcement.

3. The reinforced leading edge section for an aircraft, according to claim 2, wherein the secondary reinforcements are radially extended towards the free end of the web.

4. The reinforced leading edge section for an aircraft, according to claim 1, wherein at least one of a thickness or height of the inner reinforcement is at least twice a radius of the leading edge section.

5. The reinforced leading edge section for an aircraft, according to claim 1, wherein a thickness of the base of the inner reinforcement is different from a thickness of the web.

6. The reinforced leading edge section for an aircraft, according to claim 1, wherein the inner reinforcement is made of metallic or composite material.

7. The reinforced leading edge section for an aircraft, according to claim 1, wherein the inner reinforcement is attached to the outer skin by riveting or welding when the leading edge section is metallic, or by riveting, cobonding, or cocuring when the leading edge section is made of composite material.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0014] For a better comprehension of the invention, the following drawings are provided for illustrative and non-limiting purposes, wherein:

[0015] FIG. 1 shows a schematic view of a state of the art leading edge provided with a thickening in its outermost area.

[0016] FIG. 2 shows a schematic view of a leading edge section, according to a first embodiment of the present invention.

[0017] FIG. 3 shows a schematic view of a leading edge section, according to a second embodiment of the present invention.

[0018] FIG. 4 shows an aircraft equipped with the leading edge section of the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0019] FIG. 2 shows a reinforced leading edge section (1) for an aircraft that comprises an outer skin (2) and an inner reinforcement (3). The outer skin (2) is formed with an aerodynamic leading edge profile. The inner reinforcement (3) is arranged internally with respect to the outer skin (2) along the span of the leading edge section (1).

[0020] As shown in FIG. 2, the inner reinforcement (3) comprises a base (3′), and a web (3″) with a free end (3″a) and an opposite end (3″b) joined to the base (3′). The base (3′) has a C-shaped configuration and it is joined to the outermost part of the outer skin (2). The web (3″) is extended in a direction transverse to the direction of the span of the leading edge section (1).

[0021] This way, the invention provides a leading edge section with an improved impact behavior, a reduced weight, and easier manufacture due to the avoidance of thickness changes.

[0022] As shown in FIG. 3 and according to another preferred embodiment, the reinforced leading edge section (1) further comprises one pair of secondary reinforcements (4) attached to both ends of the base (3′) of the inner reinforcement (3) to maximize the forward mass. As shown, the secondary reinforcements (4) are preferably radially extended towards the free end of the web (3″a).

[0023] As in FIG. 2, the web (3″) of the inner reinforcement (3) is extended towards the rear part, the leaving a marginal distance to avoid any contact of the inner reinforcement (3) with the front spar (8) in the event of a bird strike.

[0024] According to another preferred embodiment, the thickness and/or height of the inner reinforcement (3) is at least twice the radius of the leading edge section (1).

[0025] According to another preferred embodiment, the thickness of the base (3′) of the inner reinforcement (3) is different from the thickness of the web (3″) in order to optimize the construction of the part.

[0026] According to another preferred embodiment, the inner reinforcement (3) is made of metallic or composite material.

[0027] According to another preferred embodiment, the inner reinforcement (3) is attached to the outer skin (2) by riveting or welding when the leading edge section (1) is metallic, or by riveting, cobonding, or cocuring when the leading edge section (1) is of composite material.

[0028] Finally, FIG. 4 shows an aircraft 10 equipped with the leading edge section (1) as described in the wings, the HTPs and the VTP.

[0029] 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.