BOX STRUCTURAL ARRANGENMENT FOR AN AIRCRAFT AND MANUFACTURING METHOD THEREOF

Abstract

A box structural arrangement (1) for an aircraft including first (2) and second composite layers (3), at least one spar web (4) extended between opposite edges of the first and second composite layers (2, 3) along a longitudinal direction, and a conduit piece (5) extended between opposite edges of the first and second composite layers (2, 3). The conduit piece (5) has a hollow section (6) comprising at least one conduit (7) dimensioned to receive pipes or harnesses and surrounded by a resilient material (8). The conduit piece (5) is mounted on the spar web (4) to provide a channeled box structural arrangement (1). The box structural arrangement can be applicable in a torsion box or a wing. The invention further refers to a method for manufacturing the box structural arrangement for an aircraft.

Claims

1. A box structural arrangement for an aircraft comprising: a first composite layer and a second composite layer; at least one spar web spanning between the first and second composite layers and extending between opposite edges of the first and second composite layers along a longitudinal direction, and a conduit piece having a hollow section comprising at least one conduit dimensioned to receive pipes and/or harnesses, and surrounded by a resilient material, wherein the conduit piece extends between the opposite edges of the first and second composite layers and is mounted on the spar web.

2. The box structural arrangement for the aircraft according to claim 1, wherein the resilient material includes a foam bed configured to support the pipes and/or harnesses.

3. The box structural arrangement for the aircraft according to claim 1, wherein the conduit piece has in cross-section an omega shape or a trapezoidal shape, and the conduit piece includes a flat mounting surface.

4. The box structural arrangement for the aircraft according to claim 1, wherein the resilient material includes foam or plastic.

5. The box structural arrangement as in claim 1, further comprising: a horizontal tail plane including an upper skin and a lower skin, a forward tail plane spar and a rear tail plane spar arranged along a spanwise direction of the horizontal tail plane, wherein the upper and lower skins form the first and second composite layers, and the at least one spar web includes respective spar webs on each of the forward tail plane spar and the rear tail plane spar, and wherein the at least one conduit piece includes a conduit piece mounted on the forward tail plane spar and another conduit piece mounted on the rear tail plane spar.

6. The box structural arrangement as in claim 1, further comprising a wing comprising an upper skin and a lower skin, a forward wing spar and a rear wing spar each arranged along a spanwise direction of the wing, wherein the upper and lower skins form the first and second composite layers, and the at least one spar web includes respective spar webs on each of the forward wing spar and the rear wing spar, and wherein the at least one conduit piece includes a conduit piece mounted the forward wing spar and another conduit piece mounted on the rear wing spar.

7. The box structural arrangement as in claim 1, wherein the arrangement further comprises: a vertical tail plane for an aircraft comprising skins on opposites sides of the vertical tail plane, a forward vertical tail plane spar, and a rear vertical tail plane spar both arranged in a spanwise direction of the vertical tail plane; wherein the skins form the first and second composite layers, and the at least one spar web includes respective spar webs on each of the forward and rear vertical tail plane spars, and wherein the at least one conduit piece includes a conduit piece mounted on the forward vertical tail plane spar and another conduit piece mounted on the rear tail plane spar.

8. A method to manufacture a box structural arrangement for an aircraft, comprising: providing a first layer of composite material and a second layer of composite material, positioning at least one spar web to span between the first and second layers of the composite material; positioning the at least one spar between opposite edges of the first and second composite layers along a longitudinal direction of the box structural arrangement; positioning a conduit piece to extend along at least a majority of a length of the at least one spar and to span the opposite edges of the first and second composite layers, wherein the conduit piece includes a hollow section which forms at least one conduit dimensioned to receive pipes and/or harnesses to be surrounded by a resilient material, and mounting the conduit piece on the at least one spar web to form a channeled box structural arrangement.

9. A torsion box for an aerodynamic component of an aircraft, the torsion box comprising: skins formed of composite layers and having outer surfaces forming an outer surface of the aerodynamic component; a spar formed of a composite material, spanning between the skins, and extending a length of the torsion box in a spanwise direction of the aerodynamic component; a hollow conduit piece formed of a composite material and on a web of the spar, wherein the hollow conduit piece extends at least a majority of the length of the spar and the conduit piece is configured to receive a pipe or harness which extends the length of the conduit piece; a resilient and deformable material in the hollow of the conduit piece, wherein the resilient and deformable material abuts inner walls of the conduit piece; and a channel within the resilient and deformable material which is parallel to the web of the spar, wherein the channel is configured to receive the pipe or harness.

10. The torsion box of claim 9, further comprising a bracket on an edge of another spar, wherein the bracket is configured to receive the pipe or harness.

11. The torsion box of claim 9, wherein the skins are an upper skin and a lower skin of a lifting surface.

12. The torsion box of claim 9 wherein the skins include a left-side skin and a right-side skin of a vertical tail plane.

13. The torsion box of claim 9 wherein the spar is a front spar and the torsion box includes a rear spar, and the conduit piece is on an outer surface of a web of the front spar which faces away from the torsion box and another conduit piece is on an outer surface of a web of the rear spar.

14. The torsion box of claim 9 wherein the spar is a front spar, the conduit piece is on an outer surface of the web of the spar and the front spar is configured to attach to a leading edge structure of the aerodynamic component.

Description

SUMMARY OF FIGURES

[0015] For a better comprehension of the invention, the following drawings are provided for illustrative and non-limiting purposes, wherein:

[0016] FIG. 1 shows a schematic view of a conventional HTP equipped with a hydraulic pipeline that crosses both HTP lateral boxes.

[0017] FIGS. 2a and 2b show a schematic front view (drawing A) and perspective view (drawing B) of a box structural arrangement of one the HTP lateral boxes of FIG. 1.

[0018] FIGS. 3a and 3b shows a schematic front view (drawing A) and perspective view (drawing B) of a box structural arrangement for an aircraft.

[0019] FIGS. 4a and 4b show a perspective view of the conduit piece (drawing A) and the conduit piece mounted on the spar web (drawing B).

[0020] FIGS. 5a and 5b show a schematic perspective view (drawing A) of an HTP equipped with the box structural arrangement, and a cross sectional view (drawing B) of the A-A axis depicted in drawing A.

DETAILED DESCRIPTION

[0021] FIGS. 3a and 3b show a box structural arrangement (1) for an aircraft, such as a lateral (torsion) box for a wing, HTP or VTP. the box structural arrangement (1) comprises first (2) and second composite layers (3), at least one spar web (4) transversely arranged between the first (2) and second composite layers (3), and a conduit piece (5) mounted on the at least one spar web (4). The first and second composite layers may be skins forming outer aerodynamic surfaces on the wing, HTP or VTP such as shown as (1).

[0022] The spar web (4) is extended between opposite edges (2a, 2b, 3a, 3b) of the first and second composite layers (2, 3) following a longitudinal direction. Thus, the spar web (4) has substantially the same length as the first (2) and second composite layers (3) to provide a continuous support to the conduit piece (5). The spar web may be embodied as a spar which is has

[0023] The conduit piece (5) is also extended between opposite edges (2a, 2b, 3a, 3b) of the first and second composite layers (2, 3). Thus, the conduit piece (5) has similar (or same) length as the spar web (4) to provide continuous encapsulation (and support) for the pipes or harnesses (19) along the box structural arrangement (1)

[0024] The pipelines or harnesses 15 may extend the spanwise length of one or more of the spars. For all or most of the length of a spar, the pipelines and harnesses are encased in respective conduits (7) of a conductive piece (5).

[0025] The spars (4) with the conduit pieces (5) may be the front and/or rear spars as shown in FIGS. 3a, 5a and 5b. In addition, a spar internal to the torsion box may also have a conduit piece, as is shown in FIG. 3b. As is shown in FIG. 3a, a torsion box (1) may have a front/rear spar (4) with a conduit piece (5) and another rear/front spar that uses mounting brackets to support the pipelines and/or harnesses.

[0026] The pipelines and/harness may also extend in a chordwise direction across edges of the spars forming the torsion box (1). As shown in FIG. 3b, the spare edges may include brackets 21 that support the pipelines and/or harnesses at an end/edge of the spar.

[0027] As shown in FIGS. 4a and 4b, the hollow section (6) of the conduit piece (5) encloses two conduits (7) (channels or canals) surrounded by a resilient material (8). The conduits (7) are dimensioned to receive pipes or harnesses (19), which will be preferably coated by a hard cover (20), e.g., sleeve, to provide rigidity and an easy insertion into the conduits (7).

[0028] The conduits (7) may include a foam bed surface (21) to ease the introduction of pipes or harnesses (19). The foam bed surface 21 may be a cylindrical surface dimensioned to slidably receive and support the hard cover (20) for the pipes or harnesses (19).

[0029] As shown in FIGS. 4a and 4b, the conduit piece (5) may have a cross-sectional shape of an omega or trapezoidal shape. The conduit piece may be integrated into the spar as shown in FIG. 4a or mounted to a surface of a web of the spar as shown in FIG. 4b. If integrated into the spar, one side of the conduit piece has a flat mounting surface (9) to facilitate its integration into the spar web (4). Alternatively and as shown in FIG. 4b, the conduit piece (5) may have an open side that is closed by a surface of the spar (4) to which the conduit piece is attached. As shown in FIG. 4b, the conduit piece (5) may be attached to the web of a spar (4) by fasteners. Alternatively, the conduit piece (5) may be integrated into the spar (4) such as by molding as a single component the spar (4) and the conduit piece (5).

[0030] The resilient material (8) may be foam, plastic or other deformable and resilient material. The resilient material (8) substantially entirely fills a cross-sectional area of the hollow channel section (6) of the conduit piece (5). The resilient material (8) includes one or more conduits (7) which are hollow sections of the resilient material (8). The resilient material may extend along the entire length of the conduit piece (5) or be arranged at various sections along the length of the conduit piece (5) such as at the ends of the conduit piece (5) and at a middle region of the conduit piece.

[0031] FIGS. 5a and 5b show a perspective and cross-sectional view of a horizontal tail plane (10). The horizontal tail plane (10) has upper (11) and lower skins (12), and forward (13) and rear spars (14) arranged along a spanwise direction. The horizontal tail plane (10) further comprises the box structural arrangement (1) described above, wherein the upper and lower skins (11, 12) comprises the first (2) and second composite layers (3), and wherein at least one conduit piece (5) is mounted on each one of the forward spars (13) and the rear spars (14).

[0032] The conduit piece (5) and the spar web (4) may extend between the shortest opposite edges of the first and second composite layers (2, 3) following a spanwise direction.

[0033] The invention may be deployed to provide an alternative installation concept that offers a clean and smooth surface for aerodynamic purposes. The potential extra weight of the conduit piece till the end of the stabilizer is compensated with the aerodynamic benefit of such a clean surface.

[0034] Similarly, the invention may be embodied within a wing or a vertical tail plane that comprises a box structural arrangement as described.

[0035] The invention may be embodied as a method for manufacturing a box structural arrangement (1) for an aircraft as described above. The method comprises the steps of:

[0036] (a) providing a first and a second layer of composite material (2, 3),

[0037] providing at least one spar web (4) extended between opposite edges (2a, 2b, 3a, 3b) of the first and second composite layers (2, 3),

[0038] (b) arranging the spar web (4) between opposite edges (2a, 2b, 3a, 3b) of the first and second composite layers (2, 3) along a longitudinal direction,

[0039] (c) providing a conduit piece (5) extended between opposite edges (2a, 2b, 3a, 3b) of the first and second composite layers (2, 3) and having a hollow section (6) (d) comprising at least one conduit (7) dimensioned to receive pipes or harnesses and surrounded by a resilient material (8),

[0040] (e) mounting the conduit piece (5) on the spar web (4) to form a channeled box structural arrangement (1).

[0041] The large and single pieces of pipelines/harnesses may be easily installed from one side in the factory. In case of stabilizers (HTP, VTP) connections/bifurcations can be done from outside their boxes, removing then the need for access panels (service doors) in the middle of these components. The potential extra weight is compensated with the cleanness of the surface that leads to aerodynamic benefits.

[0042] 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.