Aircraft composite panel assembly and manufacturing method thereof

Abstract

An aircraft composite panel assembly includes a first panel having upper and lower faces, the lower face having a recess on a first side of the panel, a second panel having upper and lower faces, the lower face having an outward projection at a first side of the panel, the outward projection received on the recess forming a lower continuous face; and a forward stack of plies of composite material bonded to the upper face of the first panel, the forward stack of plies having an edge overlapping the first side of the first panel, and the number of plies of the forward stack of plies decreasing toward the opposite side of the first side of the first panel.

Claims

1. An aircraft composite panel assembly comprising: a first panel having an upper face and lower face, the lower face having a recess on a first side of the panel; a second panel having an upper face and lower face, the lower face having an outward projection at a first side of the panel, the outward projection received on the recess of the first panel forming a lower continuous face; and a forward stack of plies of composite material bonded to the upper face of the first panel, the forward stack of plies having an edge that covers the first side of the first panel, and a number of plies of the forward stack of plies decreasing toward an opposite side of the first side of the first panel.

2. The aircraft composite panel assembly according to claim 1, wherein the lower face of the second panel has a recess at a second side opposite to the first side of the panel, and wherein the panel assembly further comprises a third panel having an upper face and lower face, the lower face having an outward projection at a first side of the panel, and wherein the outward projection is received on the recess of the second panel forming a lower continuous face.

3. The aircraft composite panel assembly according to claim 2, further comprising a rearward stack of plies of composite material bonded to the upper face of the second and third panels, wherein a number of plies of the rearward stack of plies decreases toward an opposite side of the first side of the third panel.

4. The aircraft composite panel assembly according to claim 3, wherein the rearward stack of plies has an edge that covers the first side of the third panel.

5. The aircraft composite panel assembly according to claim 3, wherein the rearward stack of plies comprises first and second plies of rectangular shape, a third ply disposed on the second ply, and a fourth ply disposed on the third ply, the third and fourth plies covering at least part of an area of the upper face of the second panel correspondent to the assembly between the recess of the second panel and the outward projection of the third panel.

6. The aircraft composite panel assembly according to claim 5, wherein the third ply has a J-shaped configuration, and the fourth ply has a Z-shaped configuration, and wherein the third and fourth plies are disposed to cover at least part of the upper edge of the third panel.

7. The aircraft composite panel assembly according to claim 1, further comprising an outer ply deposited on the panel assembly.

8. The aircraft composite panel assembly according to claim 1, wherein the forward stack of plies comprises first and second plies of rectangular shape, a U-shaped third ply disposed on the second ply, and a L-shaped fourth ply disposed on the third ply, the third and fourth plies covering at least part of an upper edge of the first panel.

9. An aircraft, comprising a landing gear door, a wing having a leading edge and a trailing edge, a horizontal tail plane having a leading edge and a trailing edge, a vertical tail plane having a leading edge and a trailing edge, a belly fairing, and a composite panel assembly, the composite panel assembly comprising: a first panel having an upper face and lower face, the lower face having a recess on a first side of the panel; a second panel having an upper face and lower face, the lower face having an outward projection at a first side of the panel, the outward projection received on the recess of the first panel forming a lower continuous face; and a forward stack of plies of composite material bonded to the upper face of the first panel, the forward stack of plies having an edge that covers the first side of the first panel, and a number of plies of the forward stack of plies decreasing toward an opposite side of the first side of the first panel; and wherein at least part of the landing gear door, and/or the leading edge of the wing, and/or the trailing edge of the wing, and/or the leading edge of the horizontal tail plane, and/or the trailing edge of the horizontal tail plane, and/or the leading edge of the vertical tail plane, and/or the trailing edge of the vertical tail plane, and/or the belly fairing comprises the composite panel assembly.

10. A method for manufacturing a composite panel assembly for an aircraft, comprising: providing a first panel having an upper face and lower face; providing a recess on a first side of the lower face of the first panel; providing a second panel having an upper face and lower face, the lower face having an outward projection at a first side of the panel; providing a forward stack of plies of composite material, the forward stack of plies having an edge and a decreasing number of plies toward an opposite side of the edge; bonding the forward stack of plies to the upper face of the first panel, such that the edge of the forward stack of plies covers the first side of the first panel; and coupling the outward projection of the second panel with the recess of the first panel forming a lower continuous face.

11. The method according to claim 10, further comprising: providing a third panel having an upper face and lower face, the lower face having an outward projection at a first side of the panel; providing a recess on the lower face of a second side opposite to the first side of the panel; and coupling the outward projection of the third panel with the recess of the second panel forming a lower continuous face.

12. The method according to claim 11, further comprising: providing a rearward stack of plies of composite material, the rearward stack of plies having a decreasing number of plies toward one of its edges; and bonding the rearward stack of plies to the upper face of both the second and third panels, such that the number of plies decreases in a direction opposite to the second panel.

13. The method according to claim 12, wherein the rearward stack of plies comprises first and second plies of rectangular shape, a third ply disposed on the second ply, and a fourth ply disposed on the third ply, the third and fourth plies covering at least part of an area of the upper face of the second panel correspondent to the assembly between the recess of the second panel and the outward projection of the third panel.

14. The method according to claim 13, wherein the third ply has a J-shaped configuration, and the fourth ply has a Z-shaped configuration, and wherein the third and fourth plies are disposed covering at least part of the upper edge of the third panel.

15. The method according to claim 11, wherein the forward stack of plies comprises first and second plies of rectangular shape, a U-shaped third ply disposed on the second ply, and a L-shaped fourth ply disposed on the third ply, the third and fourth plies covering at least part of the upper edge of the first panel.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) For a better comprehension of the disclosure herein, the following example drawings are provided for illustrative and non-limiting purposes, wherein:

(2) FIG. 1 shows a front view of a conventional composite panel assembly.

(3) FIG. 2a-2b show respectively a cross-sectional view and a front view of the known glued seal solution for assembling panels. FIG. 2a shows two panels attached by the glued seal. FIG. 2b shows one of the panels, once the glued seal has been retired.

(4) FIG. 3a-3b show respectively a front perspective view and a rear perspective view of a composite panel assembly, according to a first embodiment of the present disclosure.

(5) FIG. 4 shows a front perspective view of a composite panel assembly, according to a second embodiment of the present disclosure. FIG. 4 further shows a forward stack of plies and a rearward stack of plies, according to preferred embodiments.

(6) FIG. 5 shows a part of an aircraft, in particular, the interface between the wing and the fuselage, in which the composite panel assembly has been provided.

DETAILED DESCRIPTION

(7) FIG. 3 shows an aircraft composite panel assembly 10 according to a preferred embodiment. According to the disclosure herein, the composite panel assembly 10 comprises a first panel 1 having upper and lower faces, a second panel 2 having upper and lower faces, and a forward stack of plies 5 of composite material bonded to the upper face of the first panel 1.

(8) FIG. 3a shows the upper face of the first and second panels 1, 2, together with the forward stack of plies 5, and FIG. 3b shows the lower face of the first and second panels 1, 2.

(9) As shown in FIGS. 3a and 3b, the lower face of the first panel 1 has a recess 7 on a first side 1a of the panel 1, and the second panel 2 has an outward projection 8 on a first side 2a of the panel 2, wherein the outward projection 8 is configured to be received on the recess 7 forming a lower continuous face.

(10) To reinforce the assembly between the first and second panels 1, 2, a forward stack of plies 5 of composite material is bonded to the upper face of the first panel 1. As shown in FIG. 3a, the forward stack of plies 5 has an edge 5a overlapping the first side 1a of the first panel 1. With this positioning, in addition to provide reinforcement to the assembly, the disclosure herein allows that panels 1, 2 can be separately uninstalled. This way, the disclosure herein simplifies the installation and maintenance of conventional panel assemblies.

(11) Further, the forward stack of plies 5 is formed by a decreasing number of plies toward the opposite side of the first side 1a of the first panel 1. This configuration improves the aerodynamic response of the assembly, reducing turbulences and drag in the aircraft.

(12) FIG. 4 shows a front perspective view of a second embodiment of a composite panel assembly 10. The composite panel assembly 10 comprises a first 1, second 2 and third panels 3, and a forward 5 and backward stack of plies 6.

(13) The first and second panels 1, 2, and the forward stack of plies 5 are as already described, in which the lower face of the second panel 2 further comprises a recess 9 at a second side 2b of the panel 2, the second side 2b being opposite to the first side 2a of the panel 2.

(14) The third aircraft panel 3 has upper and lower faces. The lower face has an outward projection 11 at a first side 3a of the panel 3. The outward projection 11 of the third panel 3 is received on the recess 9 of the second panel 2 forming a lower continuous face.

(15) To reinforce the assembly between the second and third panels 2, 3 a rearward stack of plies 6 of composite material is bonded to the upper face of the second and third panels 2, 3.

(16) Further, the number of plies of the rearward stack of plies 6 decreases toward the opposite side of the first side 3a of the third panel 3. This way, the number of plies dies progressively toward the middle section (second panel) to have a smooth structural and airflow transition.

(17) As shown in FIG. 4 and according to another preferred embodiment, the forward stack of plies 5 comprises first and second plies 5, 5 of rectangular shape, a U-shaped third ply 5 disposed on the second ply 5, and a L-shaped fourth ply 5 disposed on the third ply 5, the third and fourth plies 5, 5 covering at least part of the upper edge 1c of the first panel 1.

(18) Further, as shown in FIG. 4 and according to another preferred embodiment, the rearward stack of plies 6 has an edge 6a overlapping the first side 3a of the third panel 3. Preferably, the rearward stack of plies 6 comprises first and second plies 6, 6 of rectangular shape, a third ply 6 disposed on the second ply 6, and a fourth ply 6 disposed on the third ply 6, the third and fourth plies 6, 6 covering at least part of an area of the upper face of the second panel 2 correspondent to the assembly between the recess 9 of the second panel 2 and the outward projection 11 of the third panel 3.

(19) Preferably, the third ply 6 has a J-shaped configuration, and the fourth ply 6 has a Z-shaped configuration, and wherein the third and fourth plies 6, 6 are disposed to cover at least part of the upper edge 3c of the third panel 3.

(20) Plies are placed only locally at the extremity to compensate the free edge effect, and not to influence the overall stiffness of the seal (3 or 4 plies of local reinforcement).

(21) Additionally, according to a preferred embodiment, the composite panel assembly 10 may further comprise an outer ply deposited on the panel assembly 10, embedding the stack of plies 5, 6 into the composite panel assembly.

(22) According to another preferred embodiment, the stack of plies 5, 6 are extended to cover the riveting area of the panels 1, 2, 3, to thus avoiding the opening of the flange.

(23) Further, according to another preferred embodiment, panels 1, 2, 3, are substantially made of silicone rubber, and the stacks of plies 5, 6 are substantially made of fiberglass.

(24) Finally, FIG. 5 shows a part of an aircraft, in which the interface between the upper side of the wing and the fuselage can be appreciated. As shown, a composite panel assembly 10 can be provided at the overwing seal.

(25) While at least one exemplary embodiment of the 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, an 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