AIRCRAFT CABIN PARTITION

Abstract

The invention relates to a partition for dividing an aircraft cabin into individual sections, comprising at least one opaque air passage to allow pressure equalization between the sections through the partition. Figure 1a

Description

Title of the invention: AIRCRAFT CABIN PARTITION technical field

[0001] The invention relates to a partition for an aircraft cabin. PREVIOUS STATE OF THE ART

[0002] In aircraft cabins, partitions are regularly installed to divide the cabin into sections, for example into first class and second class. They are often constructed using a sandwich structure and are relatively heavy.

[0003] Due to type-approval requirements, the bulkheads must withstand certain scenarios. For example, the bulkheads must not lose their stability in the event of a rapid drop in cabin pressure, as defined in CS-25 regulation, PAR 25.365. Because of the large surface area of ​​each bulkhead, they must be mechanically reinforced, resulting in an increase in the weight of conventional bulkheads. This increased weight not only leads to higher fuel consumption but can also necessitate further reinforcement measures that increase the weight even more.

[0004] Partitions characterized by reduced weight are presented in German patent DE 10 2009 010 861 B4 of the applicant. This document describes, among other things, modular partitions comprising a frame and a flat element stretched within the frame, such as a canvas or film. The flat element can be stretched over the entire frame or only over a portion of the frame, and a rigid flat element in the form of a plate, for example made of CFRP, can be used in the remaining portion of the frame. Description of the invention

[0005] The invention aims to create an alternative partition for an aircraft cabin that meets the requirements for type approval.

[0006] This task is solved by a partition having the characteristics of the invention.

[0007] A partition according to the invention is intended to divide an aircraft cabin into individual sections and has at least one opaque or nearly opaque air passage to allow pressure equalization between the sections through the partition. According to the invention, the partition comprises a frame and at least one flat, tension-free element inserted into the frame, the structure / construction / composition of which forms at least one air passage and / or the type of suspension of which in the frame forms at least one air passage.

[0008] According to the invention, at least one flat element forms, in a quasi-intrinsic way (structure / construction / composition), at least one air passage and / or by its type of attachment in the frame, such that in the latter, the flat element itself It can be airtight. Thanks to at least one air passage, the partition exhibits reduced structural resistance during pressure equalization, allowing it to be designed to be lighter than traditional partitions, which has a positive effect on the aircraft's fuel consumption due to its reduced weight. The opacity prevents passengers from seeing from one section to another through the flat insert. The limited-transparency construction thus preserves privacy and spatial separation between the different cabin classes. The fact that at least one flat element is tension-free means that no stress is exerted on the flat element under normal conditions. Preferably, not only is at least one flat element tension-free, but the type of suspension in the frame is also tension-free in order to reduce the necessary restraining forces on the frame.

[0009] In one embodiment, the at least one flat element consists of at least two layers, each having a plurality of air passages. The layers, preferably parallel, are arranged relative to each other such that their air passages are staggered. The air passages allow for continuous pressure equalization. Because the air passages of the layers are staggered relative to each other, light rays cannot, or can only to a limited extent, pass directly through the flat element, thus ensuring maximum opacity. Furthermore, light rays passing through the air passages of one layer can strike the other layer on the back and be reflected or scattered. It is therefore impossible to see through the at least one flat element. In addition, the layers can be coated with a light-absorbing paint on their sides facing each other.Perforated plates are an example of such layers.

[0010] In one embodiment, at least one flat element consists of a plurality of partially overlapping slats. The slats may be arranged in a single row (one layer) or in several rows (several layers). When the slats are arranged in a single row, adjacent slats overlap, like a Venetian blind. When the slats are arranged in several rows, slats adjacent to each other in a layer may be spaced apart, but opposite slats overlap.

[0011] In one embodiment, the lamellae have a V-shaped cross-section. The lamellae are preferably nested within each other in the same orientation, so that, in the case of a single-row arrangement, an overlap of both sides (i.e., of their branches) is obtained.

[0012] In another embodiment, at least one flat element is formed in the form of a porous element with a plurality of open pores acting as air passages. The pores are such that the light rays entering them are diffused into The pores. Light cannot pass through the flat surface in a straight line, just like the eye cannot. The pores allow for air balancing and therefore pressure equalization; their staggered arrangement ensures opacity.

[0013] Another embodiment of the at least one flat element provides for a plate-shaped element held in such a way that its edge can be bypassed by air, at least in part. Such a flat element may, in particular, have an airtight structure, since the pressure equalization takes place outside the flat element. For example, the edge may be surrounded by a U-shaped support, and the flat element may be held in the support by rod-shaped supports.

[0014] Preferably, at least one flat element is elastic. This feature promotes pressure equalization. The elasticity is such that, under the conditions required by the regulations, there is no destruction of at least one flat element, and it is not torn from its anchoring in the frame, even in the event of maximum rapid pressure equalization.

[0015] In order to obtain lighting effects on one side or both sides of the partition, a light insert can be integrated into at least one flat element.

[0016] In one embodiment, at least the partition frame is manufactured in a modular fashion or according to a differential construction. For example, components made of aluminum, titanium, and / or fiber composites are removably connected to each other. Such a differential construction allows for disassembly and a high degree of recyclability of the individual components. Preferably, the partition is made of one or more low-carbon materials that are also recyclable. Thus, the partition according to the invention exhibits a high degree of environmental compatibility compared to the prior art. Brief description of the drawings

[0017] Preferred embodiments of the invention are explained in more detail below with the aid of highly simplified schematic representations. Indications such as the longitudinal direction x, the transverse direction y, and the vertical direction z refer to the longitudinal, transverse, and vertical directions of an aircraft cabin or aircraft. The following figures illustrate:

[0018] [Fig.1a] is a view of an example embodiment of a partition according to the invention,

[0019] [Fig.1b] is a view of an example embodiment of a partition according to the invention,

[0020] [Fig. 1] is a view of an example of an embodiment of a partition according to the invention,

[0021] [Fig.2] is a frame of the partition according to the invention in a construction differential,

[0022] [Fig.3a] shows a rounding of the interior space angles or the space angles intermediate of the framework,

[0023] [Fig.3b] shows an angle insert for rounding,

[0024] [Fig.4a] shows preferred flat elements of the partition according to the invention in cross-section,

[0025] [Fig.4b] shows preferred flat elements of the partition according to the invention in cross-section,

[0026] [Fig.4c] shows preferred flat elements of the partition according to the invention in cross-section, and

[0027] [Fig.4d] shows preferred flat elements of the partition according to the invention in cross-section.

[0028] DETAILED STATEMENT OF IMPROVEMENTS

[0029] Figures 1a, 1b and 1e show a first example of an embodiment of a partition 1 according to the invention. The partition 1 serves to unilaterally divide an aircraft cabin into several sections, for example into first class and second class.

[0030] Fig. 1a shows a plan view in the longitudinal direction x from the rear towards the front in the aircraft cabin. [Fig.lb] shows a side view in the transverse y direction of the aircraft cabin from the inside out and [Fig. le] shows a plan view in the longitudinal x direction from front to back in the aircraft cabin.

[0031] The partition shown here is arranged on the right in the aircraft cabin and fixed by means of lower fixings 2a, 2b in rails on the floor and by means of at least one upper fixing 4 to a rear structure of the aircraft cabin.

[0032] The partition 1 includes a frame 8 for stabilization and, here, two flat tension-free elements 10a, 10b, which are inserted respectively into an intermediate space or a receiving opening 12a 12b of the frame 8.

[0033] The partition 1 is manufactured using a differential construction from a plurality of individual components, which facilitates recycling and also allows for reuse. Thus, the frame 8, for example, is modularly composed of a plurality of frame profiles 14a, 14b, 14c which delimit an interior frame space in the transverse direction y and in the vertical direction z. It forms a demountable frame in its frame profiles 14a, 14b, 14c.

[0034] A passenger panel 16 is inserted into the frame 8 and extends transversely between the two lateral frame profiles 14a, 14b. The passenger panel 16 is intended, for example, for the arrangement of screens, tablets, and the like, and is located at eye level for a passenger seated directly in front of the partition 1 in a section. It divides the interior frame space into the upper intermediate space 12a and the lower intermediate space 12b. As illustrated in [Fig. 2], the passenger panel 16 can have different heights.

[0035] As shown in figures 1a and 1e, one of the flat elements 10a, 10b is inserted over the entire surface in each of the intermediate spaces 12a, 12b. In example In the embodiment presented here, the flat elements 10a, 10b are air-permeable but opaque or largely opaque. Each flat element 10a, 10b allows for air exchange and thus rapid pressure equalization between the sections. Preferably, the flat elements 10a, 10b extend over the entire interior frame space, except for one passenger panel area. If no passenger panel 16 is installed, only one flat element 10a or 10b can be provided, which then occupies the entire interior frame space. A detailed description of these flat elements 10a, 10b, as well as an explanation of other tension-free flat elements 18, 20, 22, are provided in Figures 4a to 4d. The type of suspension of the flat elements 10a, 10b, 18, 20, 22 in the respective frame 8 is also preferably tension-free.

[0036] As shown in [Fig.3a], angle inserts 23 presented in [Fig.3b] can be used to round the corners of the frame interior space or intermediate spaces 12a, 12b, which inserts have a hollow groove 25 oriented towards the respective intermediate space 12a, 12b.

[0037] As illustrated in [Fig. 4a], the flat elements 10a, 10b have a construction or structure comprising two layers 24a, 24b spaced apart in the longitudinal direction x of the aircraft. There is air between the layers 24a, 24b. Each layer 24a, 24b has a plurality of openings in the form of individual air passages 26a, 26b, through which air exchange or pressure equalization can take place (dashed arrows 31). The layers 24a, 24b are, for example, perforated plates. The layers 24a, 24b are arranged relative to each other in such a way that the air passages 26a, 26b are arranged in offset relative to each other, that is to say that light rays 30 cannot pass directly through the flat elements 10a, 10b, but after passing through the air passages 26a of one layer 24a, they strike the inner side 28 of the other layer 24b between the air passages 26b of the latter..

[0038] Of course, it is possible to provide for more than two layers 24a, 24b.

[0039] Figure 4b shows a flat, air-permeable, opaque element 18 with a different type of structure. This flat element 18 has a plurality of lamellae 32, 34. The lamellae 32, 34 have a V-shaped cross-section with two branches 32a, 32b and 34a, 34b. They are nested (interlocked) with each other, for example in the vertical direction z of the aircraft cabin, such that their tips 36 overlap in a vertical plane and the branches 32a, 34a or 32b, 34b of the adjacent lamellae 32, 34 overlap. An air passage 26a is thus formed between the neighboring slats 32, 34, the overlap of the two sides preventing the light rays 30 from passing from one side of the partition 1 to the other side of the partition 1 (detailed representation on [Fig.4b]).

[0040] The flat, air-permeable, and opaque element 20 shown in [Fig. 4c] has a porous structure and is therefore made in the form of a porous element with a plurality of pores 38a to 38e as air passages 26a (detailed representation in [Fig. 4c]). The arrangement of the pores 38a to 38e is such that light rays 30 are scattered within the pores 38a to 38e and therefore cannot directly reach the other side of the partition 1.

[0041] Figure 4d shows a flat element 22 with a construction or structure that is itself airtight and opaque or very largely opaque. It has the shape of a plate and is held in a support 40 (suspension) of the frame 8 such that its edge 42 can be bypassed by air. Air passages 26a, 26b are thus created between the edge 42 of the flat element 22 and the support 40. For this purpose, the support 40 has a U-shaped profile with two parallel arms 44a, 44b and a connecting portion 46 linking the arms 44a, 44b together. The flat element 22 is spaced from the arms 44a, 44b and the connecting part 46. The flat element 22 can be fixed in the support 40 using similar, unshown, spacers. The arms 44a, 44b are themselves opaque, so this flat element 22 is also opaque in the area of ​​the support 40.

[0042] All the flat elements 10a, 10b, 18, 20, 22 are elastic, such that they can yield elastically in the event of pressure equalization. Elasticity may be an intrinsic property of the flat elements 10a, 10b, 18, 20, 22, but it may also be obtained or supplemented by elastic support in the frame 8.

[0043] In particular, a luminous insert can be integrated into the air-permeable flat elements 10a, 10b, 18, 22 to obtain a specific lighting effect on one or both sides. In the case of the non-transparent flat element 22, such a luminous insert must be positioned in the area of ​​the support 40. It should be noted that the air-permeable flat elements 10a, 10b, 18, 20, 22 can also be held in a support 40 according to the flat element 22, such that their respective edges are also surrounded by air, thus forming an additional air passage on the outer edge.

[0044] The invention relates to a partition intended to divide an aircraft cabin into individual sections, comprising at least one opaque air passage to allow pressure equalization between the sections through the partition.

[0045] List of references

[0046] 1 Partition

[0047] 2a, b Lower fixings

[0048] 4 Upper Fixings

[0049] 8 Frame (modular, in several parts)

[0050] 10a, b Flat element

[0051] 12a, b Intermediate space

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[0077] 14a, b, c Frame profile 16 Passenger panel 18 Flat element 20 Flat element 22 Flat element 23 Corner insert 24a, b Layer 25 Recessed groove 26a, b Air passage 28 Inner side 30 Light beam 32 Slat 31 Exchange Air duct 32a, 34b Branch 34 Lamella 24a, 34b Branch 36 Tip 38a to 38e Pores 40 Support 42 Edge 44a, b Branch 46 Connecting section 50 Reinforcements / Internal structure X Longitudinal direction of the aircraft cabin Y Transverse direction of the aircraft cabin Z Vertical direction of the aircraft cabin

Claims

Demands

1. Partition (1) for dividing an aircraft cabin into individual sections, comprising at least one opaque or very largely opaque air passage (26a, 26b) to permit pressure equalization between sections through the partition (1), the partition (1) comprising a frame (8) and at least one flat, tension-free element (10a, 10b, 18, 20) inserted into the frame (8), the structure and / or type of suspension of which in the frame (8) forms at least one air passage (26a, 26b).

2. Partition according to claim 1, wherein at least one flat element (10a, 10b) is composed of at least two layers (24a, 24b, 18, 20) each having a plurality of air passages (26a, 26b, 18, 20) which are arranged relative to each other such that the air passages (26a, 26b) of the layers (24a, 24b) are arranged offset from each other.

3. Partition according to claim 1, wherein at least one flat element (18) is formed of a plurality of partially overlapping slats (32, 34).

4. Partition according to claim 3, wherein the slats (32, 34) have a V-shaped cross-section.

5. Partition according to claim 1, wherein at least one flat element (20) has a plurality of open pores (38a to 38e) as air passages (26a, 26b), light rays (30) penetrating the pores (38a to 38e) being diffused into the pores (38a to 38e).

6. Partition according to claim 1, wherein at least one flat element (22) has a peripheral edge (42) which is arranged in a U-shaped support (40) such that at least a part of the edge can be bypassed by air.

7. Partition according to any one of the preceding claims, in which a light insert is inserted into at least one flat element (10a, 10b, 18, 20).

8. Partition according to any one of the preceding claims, wherein at least the frame (8) is of modular design.

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