AIRCRAFT REAR FUSELAGE SECTION AND MANUFACTURING METHOD THEREOF

Abstract

A lower fuselage shell for an aircraft rear fuselage section, wherein the lower fuselage shell is made of a composite material and comprises at least one lower skin and stringers integrally formed with the lower skin, and frame segments extending crosswise relative to the stringers. Shear-ties are co-cured or co-bonded with the lower skin and extend crosswise relative to the stringers. Frame segments are fastened to the shear-ties, such that the frame segments are distanced from the lower skin. An aircraft rear fuselage section comprises an upper fuselage shell and the described lower fuselage shell. The upper fuselage shell has an upper skin reinforced with omega-shaped stringers, and the lower shell has a lower skin reinforced with T-shaped stringers.

Claims

1. A lower fuselage shell for an aircraft rear fuselage section, wherein the lower fuselage shell is made of a composite material and comprises: at least one lower skin, stringers integrally formed with the lower skin and extending longitudinally with respect to a longitudinal direction of the rear fuselage section, frame segments extending crosswise relative to the stringers, and composite shear-ties integrally formed with the lower skin and extending crosswise relative to the stringers, the frame segments being fastened to the shear-ties, such that the frame segments are distanced from the lower skin.

2. The lower fuselage shell according to claim 1, wherein at least one of the stringers or the shear-ties are co-cured or co-bonded with the lower skin.

3. The lower fuselage shell according to claim 1, wherein the frame segments are riveted or bolted to the shear-ties.

4. The lower fuselage shell according to claim 1, wherein the frame segments are Z-shaped.

5. The lower fuselage shell according to claim 1, wherein the stringers are T-shaped.

6. The lower fuselage shell according to claim 1, wherein the lower skin has an access opening and two beams to reinforce an area around the access opening, wherein the beams are joined to the skin and extend longitudinally.

7. An aircraft rear fuselage section comprising an upper fuselage shell and the lower fuselage shell defined in claim 1, wherein the upper and lower fuselage shells are attached to each other to configure together the rear fuselage section, and wherein the upper fuselage shell has an upper skin and omega-shaped stringers integrally formed with the upper skin and extending longitudinally, and frame segments extending crosswise relative to the omega-shaped stringers.

8. The aircraft rear fuselage section according to claim 7, wherein the upper shell has two lateral cut-outs for receiving and allowing trimming of a horizontal tail plane, each one of these cut-outs define a U-shaped edge having upper and lower edges and a vertical edge, and the lower shell extends generally from the lower edge of one lateral cut-out, to the lower edge of the other cut-out.

9. A method for manufacturing a rear fuselage section for an aircraft, comprising the steps: manufacturing a lower fuselage shell including a lower skin having an internally reinforcing structure, a manufacturing an upper fuselage shell including an upper skin having an internally reinforcing structure, producing the lower skin by means of a first technique of layering composite materials, producing the upper skin by means of a second technique of layering composite materials which is different from the first technique, and assembling the lower and upper fuselage shells to form together the rear fuselage section.

10. The method according to claim 9, wherein the first technique of layering composite materials is Fiber Placement, and wherein the second technique comprises a modular manufacturing technology.

11. The method according to claim 9, wherein the steps of manufacturing the lower and upper shells, comprises co-curing or co-bonding T-shaped stringers to the lower skin, and co-curing or co-bonding omega-shaped stringers to the upper skin.

12. The method according to claim 11, wherein the step of manufacturing the lower fuselage shell comprises co-curing or co-bonding shear-ties to the lower skin, such that the shear-ties are arranged crosswise to the stringers, and riveting or bolting frames segments to the shear-ties, such that the frame segments are distanced from the skin.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Preferred embodiments of the invention, are henceforth described with reference to the accompanying drawings, wherein:

[0033] FIG. 1 shows a side elevational view of an aircraft according to the prior-art, wherein the rear fuselage section is marked as a darkened area.

[0034] FIG. 2 shows a perspective view of a rear fuselage section according to the invention. Upper and lower shells are identified in the figure. The stringers, frame segments and shear ties are shown as enlarged details at the right hand side of the figure. The extended view of the frame segments and shear ties, is a cross-sectional view according to a longitudinal plane.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0035] FIG. 2 shows a preferred embodiment of a rear fuselage section (1) formed by an upper fuselage shell (1a) and a lower fuselage shell (1b) assembled to each other to configure together the rear fuselage section. The upper fuselage shell (1a) has an upper skin (4a) and omega-shaped stringers (5) integrally formed with the upper skin (4a) and extending longitudinally. Frame segments (6a) extend crosswise relative to the stringers (5) and are fastened directly to the skin.

[0036] The lower fuselage shell (1b) comprises a lower skin (4b) and T-shaped stringers (7) integrally formed with the lower skin (4b) and extending longitudinally. Frame segments (6b) extend crosswise relative to the T-shaped stringers (7). The lower fuselage shell (1b) further comprises composite shear-ties (8) integrally formed with the lower skin (4b) and extending crosswise relative to the T-shaped stringers (7). The frame segments (6b) are mechanically fastened (riveted or bolted (12)) to the shear-ties (8), such that the frame segments (6b) are distanced from the lower skin (4b).

[0037] Preferably, the frame segments (6b) are Z-shaped.

[0038] The stringers (5,7) of the upper and lowers shells (1a,1b) are co-cured or co-bonded with the upper and lower skins (4a,4b). Similarly, the shear-ties (8) are co-cured or co-bonded with the lower skin (4b).

[0039] The upper shell (1a) has two lateral cut-outs (11,11) for receiving and allowing trimming of a horizontal tail plane (3) (as shown in FIG. 1). Each one of these cut-outs (11,11) define a U-shaped edge having upper and lower edges and a vertical edge. As shown in FIG. 2, the lower shell (1b) generally extends from the lower edge of one lateral cut-out to the lower edge of the other cut-out.

[0040] The lower skin (4b) has an access opening (9), and two longitudinally extending beams (10) joined to the skin, to reinforce an area around the access opening (9).

[0041] 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.