AIRCRAFT STRUCTURE

Abstract

An aircraft structure which extends along a longitudinal axis, a lateral axis and a vertical axis, wherein the aircraft structure includes an upper shell and a lower shell that together surround an interior compartment designed for accommodating an aircraft cabin, and a pillar arrangement with at least one support pillar which extends through the interior compartment and connects the upper shell to the lower shell and supports same in relation to each other. An aircraft structure can be provided which is particularly efficient, in particular has a low weight and requires little space and outlay on assembly is achieved in that the interior of the support pillar has at least one flow duct for the conduction of air-conditioned air.

Claims

1. An aircraft structure which extends along a longitudinal axis, a lateral axis and a vertical axis, the aircraft structure comprising: an upper shell and a lower shell that together surround an interior compartment for accommodating an aircraft cabin; a pillar arrangement having at least one support pillar which extends through the interior compartment and connects the upper shell to the lower shell and supports same in relation to each other; and the support pillar having an interior which has at least one flow duct for m the conduction of air-conditioned air.

2. The aircraft structure according to claim 1, wherein the support pillar extends in a longitudinal central plane defined by the longitudinal axis and the vertical axis.

3. The aircraft structure according to claim 1, wherein the support pillar extends parallel to the vertical axis.

4. The aircraft structure according to claim 1, wherein the interior of the support pillar has at least two flow ducts or has at least four flow ducts.

5. The aircraft structure according to claim 4, wherein the support pillar has a round cross section, and wherein at least two, or at least four, flow ducts are arranged next to one another in two rows each having two flow ducts.

6. The aircraft structure according to claim 4, wherein the support pillar has an elongate cross section, and wherein at least two, or at least four flow ducts are in a row next to one another.

7. The aircraft structure according to claim 1, wherein the support pillar comprises a support structure for supporting the upper shell in relation to the lower shell, and a pipe structure which forms the at least one flow duct.

8. The aircraft structure according to claim 7, wherein the pipe structure is formed integrally with the support structure.

9. The aircraft structure according to claim 7, wherein the pipe structure is formed separately from the support structure.

10. The aircraft structure according to claim 9, wherein the support structure has at least two separate chambers, and wherein at least one pipe, or at least two pipes, of the pipe structure is or are arranged in each chamber.

11. The aircraft structure according to claim 1, wherein the support pillar is connected to the upper shell via diagonal support struts, and wherein four support struts are provided and are arranged such that in each case two support struts are arranged opposite each other.

12. The aircraft structure according to claim 1, wherein the support pillar is formed from fiber composite material.

13. An aircraft comprising an aircraft structure according to claim 1.

14. The aircraft according to claim 13, further comprising: an aircraft cabin in the interior compartment of the aircraft structure; an air-conditioning system having an air outlet for providing air-conditioned air; and at least one air-distributing duct on or in a ceiling of the aircraft cabin for distributing air-conditioned air in the aircraft cabin; wherein the air outlet of the air-conditioning system is connected to an inlet of the flow duct; and wherein the air-distributing duct is connected to an outlet of the flow duct.

15. The aircraft according to claim 14, wherein the air-conditioning system is configured for providing different air-conditioned air of different air-conditioning zones, wherein the air-conditioning system has a first air outlet for providing first air-conditioned air for a first air-conditioning zone and a second air outlet for providing second air-conditioned air for a second air-conditioning zone, wherein the first air outlet is connected to an inlet of a first flow duct for the first air-conditioning zone, wherein the second air outlet is connected to an inlet of a second flow duct for the second air-conditioning zone, wherein a first air-distributing duct for the first air-conditioning zone is connected to an outlet of the first flow duct, and wherein a second air-distributing duct for the second air-conditioning zone is connected to an outlet of the second flow duct.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Example embodiments of the disclosure herein will be explained in more detail below with reference to a drawing. In the drawings:

[0022] FIG. 1 shows an aircraft according to one embodiment of the disclosure herein;

[0023] FIG. 2 shows a perspective view of the interior compartment of the aircraft from FIG. 1 looking at the flow ducts and air-distributing ducts for conducting and distributing the air-conditioned air in the interior compartment or in the aircraft cabin;

[0024] FIG. 3 shows a perspective view of a support pillar according to a first embodiment of the disclosure herein;

[0025] FIG. 4 shows a plan view from below of the support pillar from FIG. 3;

[0026] FIG. 5 shows a perspective view of a support pillar according to a second embodiment of the disclosure herein;

[0027] FIG. 6 shows a plan view from below of the support pilar from FIG. 5;

[0028] FIG. 7 shows a perspective view of a detail of the aircraft structure of the aircraft from FIG. 1 with four support pillars according to the embodiment from FIG. 5; and

[0029] FIG. 8 shows the aircraft structure from FIG. 7 with coverings around the support pillars.

DETAILED DESCRIPTION

[0030] FIG. 1 illustrates an aircraft 1 according to one example embodiment of the disclosure herein. The aircraft 1 is an aircraft similar to a flying wing aircraft with an interior compartment 3 of large width.

[0031] The aircraft 1 comprises an aircraft structure 5 which extends along or parallel to a longitudinal axis 7 from a nose 9 as far as a rear 11, a lateral axis 13 between two opposite wing tips 15, and a vertical axis 17 between an upper side 19 and a lower side 21. The aircraft structure 5 comprises an upper shell 23 in the region of the upper side 19 and a lower shell 25 in the region of the lower side 21 that together surround an interior compartment 3 which is designed for accommodating an aircraft cabin 27. The aircraft structure 5 furthermore comprises a pillar arrangement 29 with a plurality of support pillars 31 which extend through the interior compartment 3 and connect the upper shell 23 to the lower shell 25 and support same in relation to each other or hold same on each other. The interior of the support pillars 31 has flow ducts 33 for the conduction of air-conditioned air of an air-conditioning system 35 which extends parallel to the longitudinal direction of the support pillars 31, as shown in FIG. 2.

[0032] The aircraft 1 furthermore comprises an aircraft cabin 27 in the interior compartment 3 of the aircraft structure 5, an air-conditioning system 35 with an air outlet 37 for providing air-conditioned air for supplying the aircraft cabin 27, and a plurality of air-distributing ducts 39 which are arranged on or in the ceiling of the aircraft cabin, with openings to the cabin compartment for distributing air-conditioned air in the aircraft cabin 27, as illustrated in FIG. 2. The air outlet 37 of the air-conditioning system 35 is connected to an inlet 39 of the flow ducts 33 at the lower end of the support pillars 31. The air-distributing ducts 39 are connected to outlets 43 of the flow ducts 33 at the upper end of the support pillars 31.

[0033] As likewise shown in FIG. 2, the air-conditioning system 35 is configured for providing different air-conditioned air of different air-conditioning zones, wherein the air-conditioning system 35 has a first air outlet 37a for providing first air-conditioned air for a first air-conditioning zone 45a, and a second air outlet 37b for providing second air-conditioned air for a second air-conditioning zone 45b. The first air outlet 37a is connected to an inlet 41 of a first flow duct 33a for the first air-conditioning zone 45a, and the second air outlet 37b is connected to an inlet 41 of a second flow duct 33b for the second air-conditioning zone 45b. A first air-distributing duct 39a for the first air-conditioning zone 45a is connected to an outlet 43 of the first flow duct 33a, and a second air-distributing duct 39a for the second air-conditioning zone 45b is connected to an outlet 43 of the second flow duct 33b. In the present example embodiment from FIG. 2, in addition to the first and second air-conditioning zone a third and a fourth air-conditioning zone are also provided which are formed analogously to the first and second air-conditioning zones.

[0034] As can be seen in FIGS. 3 through 6, the interior of the support pillars 31 has four flow ducts 33. In each case two flow ducts 33 are provided here for different air-conditioning zones. In the embodiment shown in FIGS. 3 and 4, the support pillars 31 have a circular cross section. Four flow ducts 33 are arranged next to one another here in a square shape in two rows each having two flow ducts 33. In the alternative embodiment shown in FIGS. 5 and 6, the support pillars 31 have an elongate, oval cross section. In this case, four flow ducts 33 are arranged in a row next to one another. Alternatively, it is, however, also possible for only two flow ducts 33 to be arranged next to each other.

[0035] The support pillars 31 comprise a support structure 47 for supporting the upper shell 23 in relation to the lower shell 25, and a pipe structure 49 which forms the at least one flow duct 33. In the example embodiments shown in FIGS. 3 to 6, the pipe structure 49 is formed separately from the support structure 47, wherein the individual pipes of the pipe structure 49 are accommodated in corresponding openings of the support structure 47. The support structure 47 is formed from fiber composite material, in particular from cured prepreg layers.

[0036] The support structure 47 has two chambers 51 which are separated from each other by material of the support structure 47, as can be seen in FIGS. 3 through 6. Two pipes 53 of the pipe structure 49 are arranged in each chamber 51. The two chambers 51 are assigned to different air-conditioning zones. In the example embodiments shown in FIGS. 3 through 6, it is likewise possible and preferred that, at least over part of the length of the support pillars 31, the two chambers 51 form the flow ducts 33, and the pipes 53 are connected only subsequent to the chambers, with it being possible for that part of the pipes 53 which extends through the chambers 51 to therefore be saved.

[0037] As illustrated in FIGS. 3, 5 and 7, the support structure 47 is connected to the upper shell 23 via diagonal support struts 55. Four support struts 55 are provided and arranged here in such a manner that in each case two support struts 55 are arranged opposite each other, and the support struts 55 are each fastened to the support pillar 31 at a distance of 90° in the circumferential direction around the support pillar 31. FIG. 5 additionally illustrates a central support strut 55 which connects the support structure 47 to the upper shell 23 centrally between the diagonal support struts 55.

[0038] FIG. 7 illustrates a pillar arrangement 29 with four support pillars 31, which are arranged in a row, of the embodiment shown in FIGS. 5 and 6. The support pillars 31 extend in a longitudinal central plane defined by the longitudinal axis 7 and the vertical axis 17. Furthermore, the support pillars 31 extend parallel to the vertical axis 17.

[0039] FIG. 8 illustrates the support pillars 31, which are shown in FIG. 7, with a covering 57 which peripherally covers the support structure 47 and the support struts 55 and insulates same in terms of heat and sound in relation to the aircraft cabin 27.

[0040] With the disclosure herein described above, the flow duct 33 which is provided for conducting air-conditioned air is integrated in the support pillar 31. Separate air-conditioning pipes between cabin wall and outer skin are no longer required, and therefore space, weight and outlay on assembly can be saved.

[0041] While at least one example 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 example 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 benefit or priority.