Decompression panel for aircraft, aircraft inner wall provided with such decompression panel, and corresponding aircraft

Abstract

The invention provides a pressure reduction panel for an aircraft, an aircraft inner wall provided with such a pressure reduction panel and a corresponding aircraft. The pressure reduction panel comprises a frame provided with an opening; a flap connected to the frame by a connection system, the connection system comprising at least one elastomeric part provided with a plurality of securing elements securing the part, the frame and the flap together, the flap being movable from a closed position, in which the flap completely closes the opening, to an open position, in which the flap completely closes the opening, in the open position, the flap partially releases the opening due to the action of the pressure difference between the two sides of the pressure-reducing panel in the case of rapid pressure reduction, and the elastomeric part makes it possible to obtain a pressure-reducing panel which is effective, simple to produce, free of the use of complex mechanisms, and can be used as a pressure-reducing device. And the flap can directly return to its closed position when the pressure condition is allowed again.

Description

Technical Field

[0001] The present invention relates to a pressure relief panel for an aircraft, an inner wall of an aircraft provided with such a pressure relief panel, and a corresponding aircraft. Background Art

[0002] It is known that an aircraft (especially a commercial aircraft) includes pressurized areas, especially the cabin, where the pressure generated is higher than the external pressure when the aircraft is flying at high altitude.

[0003] An aircraft generally includes a plurality of separately pressurized areas, such as the cabin and cargo hold of a commercial aircraft or the cargo area and mail area of a cargo aircraft.

[0004] In the case of decompression of one of the pressurized areas, a pressure difference is generated between the area undergoing decompression and the adjacent pressurized area. A pressure relief panel is usually provided in one or more walls separating the two adjacent areas to particularly prevent damage to the one or more partition walls due to this pressure difference.

[0005] The purpose of such a pressure relief panel is to provide protection in the case of rapid decompression, that is, in the case of a rapid change in the pressure in the area where a pressure difference is generated between two adjacent areas of the aircraft. Rapid decompression can be generated by the decompression of a pressurized area or by any other change in the pressure in the relevant area of the aircraft.

[0006] Such a pressure relief panel generally includes a frame provided with an opening and a flap connected to the frame by a mechanical system. The flap is configured to move from a closed position, in which the flap completely closes the opening, to an open position, in which the flap releases the opening due to the pressure difference generated by rapid decompression between the two sides of the panel.

[0007] The pressure relief panel can be produced in different ways. However, all common pressure relief panels require a complex mechanism with multiple mechanical components, which are designed to hold the flap in the closed position, generate its movement when the flap opens, and hold the flap after it opens so that the flap remains connected to the wall in which it is installed.

[0008] The disadvantage of such a pressure relief panel is that in the case of rapid decompression, it is necessary to return the flap to its closed position and reset the holding and opening mechanism so that the flap is operable again.

[0009] Therefore, it is necessary to find a solution for reducing and simplifying the operation of the pressure relief panel after rapid decompression. Summary of the Invention

[0010] The object of the present invention is to propose a solution to address the above needs. The present invention relates to a pressure relief panel for an aircraft, said pressure relief panel comprising at least:

[0011] - a frame provided with an opening; and

[0012] - a flap connected to the frame by a connection system, the flap being able to take at least one of two positions: a closed position and at least one open position, in the closed position, the flap completely closes the opening, in the at least one open position, the flap at least partially releases the opening, the flap being adapted to move from the closed position to the open position under the action of the pressure difference between the two sides of the pressure relief panel.

[0013] According to the invention, the flap and the frame are configured to be superimposed on at least one superimposed area, and the connection system comprises at least one elastomeric member, the at least one elastomeric member being arranged on one of the faces of said superimposed area and provided with a plurality of fixing elements, the fixing elements passing through the elastomeric member, the frame and the flap and fixing the elastomeric member, the frame and the flap together.

[0014] Since this elastomeric member connects the flap to the frame, in the case of a pressure difference between the two sides of the pressure relief panel due to a rapid decompression, the elastomeric member is thus compressed, which results in a movement of the flap relative to the frame in such a way as to move the flap into its open position and create a gap between the two elements through which air can pass, which makes it possible to reduce said pressure difference and limit the risk of damage to the dividing wall.

[0015] Furthermore, when the pressure difference decreases again, the elastomeric member returns to its initial nominal shape (due to its inherent elasticity), thus causing the flap to return to its closed position.

[0016] Therefore, no complex mechanical mechanisms or systems are used to move the flap into the open position or to move the flap back to its closed position thereafter. Furthermore, in the closed position, the flap is again directly operable and reusable.

[0017] Moreover, after a rapid decompression, no resetting action or operation is required other than a simple inspection of the pressure relief panel.

[0018] The pressure relief panel also has other advantages as specified below.

[0019] The pressure relief panel is advantageously configured such that if the pressure difference between the two sides of the frame of the pressure relief panel exceeds a predetermined value when the pressure on the side of the frame where the flap is arranged is lower, the elastomeric member is compressed in order to create a movement of the flap away from the frame and thus create an air passage between the flap and the frame.

[0020] In addition, each of the fixing elements advantageously passes through holes in the elastomeric member, the frame, and the flap, so that when the elastomeric member is compressed by the action of a pressure difference, the elastomeric member, the frame, and the flap can slide on the fixing elements and allow the flap to move away from the frame.

[0021] In addition, the decompression panel is preferably configured such that the air passage produced when the flap is in the open position has a total surface area that is substantially equal to the surface area of the opening of the frame.

[0022] In a preferred embodiment, the elastomeric member is a solid elongate member provided with a plurality of holes, each of which is intended to receive a fixing element. The elastomeric member is advantageously one of the following shapes: straight shape, curved shape.

[0023] In addition, in a particular embodiment, the flap has a rectangular shape, and the decompression panel includes at least a pair of identical elastomeric members arranged along opposite sides of the rectangular shape.

[0024] In addition, in a preferred embodiment, the decompression panel includes at least one metal plate provided with holes for the fixing elements to pass through, and the metal plate is arranged on the surface of the elastomeric member opposite to the surface in contact with the overlapping area.

[0025] In addition, the elastomeric member is advantageously provided with a housing for receiving the metal plate.

[0026] The present invention also relates to an inner wall of an aircraft, which is intended to be arranged between two adjacent zones of the aircraft, in particular between separately pressurized zones.

[0027] According to the present invention, the inner wall includes at least one decompression panel as described above.

[0028] The present invention further relates to an aircraft, particularly a commercial aircraft, which includes at least one decompression panel as described above and / or at least one inner wall as described above. Description of the Drawings

[0029] The drawings illustrate how the present invention can be implemented. In these figures, the same reference numerals denote similar elements.

[0030] Figure 1 is a partial perspective view of an interior part of an aircraft, showing a part of a wall equipped with a decompression panel according to an embodiment of the present invention.

[0031] Figure 2 represents a perspective view of the decompression panel as seen from a first side, with the flap in the closed position.

[0032] Figure 3 is a view similar to Figure 2 in which the flap is in the open position.

[0033] Figure 4 is a perspective view of the pressure relief panel as seen from a second side opposite the first side Figure 3 thereof.

[0034] Figure 5 is an exploded perspective view of an elastomeric member and an element for fixing this elastomeric member.

[0035] Figure 6 is a cross-sectional view of the pressure relief panel in which the flap is in the closed position.

[0036] Figure 7 is a view similar to Figure 6 in which the flap is in the open position.

[0037] Figure 8 is a schematic perspective view of an aircraft including a wall provided with a pressure relief panel. DETAILED DESCRIPTION

[0038] In Figures 2 to 4 a particular embodiment schematically represented, the illustrative pressure relief panel 1 of the invention is intended to be installed in the inner wall 2 of an aircraft 3, in particular a commercial aircraft, as Figure 8 partially and schematically shown therein.

[0039] More precisely, the pressure relief panel 1 is intended to be installed in the inner wall 2 which separates two adjacent zones of the aircraft, in particular two pressurized zones of the aircraft, which adjacent zones are pressurized separately, such as the cabin and the cargo hold of a commercial aircraft or the cargo area and the mail area of a cargo aircraft.

[0040] In Figure 1 a part of the interior 4 of the aircraft 3 is highly schematically represented, in which the inner wall 2 is partially shown.

[0041] As Figures 2 to 4 shown, the pressure relief panel 1 includes a frame 5 provided with an opening 6. The frame 5 may be a frame dedicated to the production of the pressure relief panel 1 or preferably may correspond to a part of the wall 2 surrounding the opening 6, as in the example of Figures 2 to 4 In this example, the opening 6 is a rectangle having a length L1 and a width L2 ( Figure 2 ).

[0042] The pressure relief panel 1 installed in the inner wall 2 further includes a flap 7 connected to the frame 5 by a connection system 8 described below.

[0043] The flap 7 can take (alternately) one or the other of the following two positions:

[0044] - A closed position P1, in which the flap completely closes the opening 6, as Figure 2 represented; and

[0045] - At least one open position P2, in which the flap partially releases the opening 6, as Figure 3 and Figure 4 represented.

[0046] Figure 3 View corresponding to one side 9 of the pressure relief panel 1 (like Figure 2 ), while Figure 4 corresponds to the view of the other side 10 of the pressure relief panel 1.

[0047] Due to the action of the pressure difference between the two sides 9 and 10 of the pressure relief panel 1, the flap 7 can move from the closed position P1 to the open position P2, as described below.

[0048] In addition, the flap 7 has a size such that it overlaps the frame 5 on at least one overlapping area 11 around the opening 6.

[0049] In the Figures 2 to 4 example, the flap 7 has a rectangular shape (including two short sides 7A and 7B and two long sides 7C and 7D, as Figure 4 shown). The overlapping area 11 (which is represented by a dashed line in Figures 2 to 4 ) is provided all around the flap 7. The overlapping area 11 (where the flap 7 overlaps the frame 5) includes four parts 11A, 11B, 11C, and 11D ( Figure 2 ), which are respectively located at the levels of the sides 7A, 7B, 7C, and 7D ( Figure 4 ).

[0050] In its closed position P2, the flap 7 contacts the frame 5 on the surfaces corresponding to the (rectangular-shaped) parts 11A, 11B, 11C, and 11D of the overlapping area 11.

[0051] In addition, the connecting system 8 includes at least one elastomeric member 13. In the Figures 2 to 4 example, the connecting system 8 includes two members 13. Each of the members 13 is arranged on the corresponding part of the parts 11A and 11B of the overlapping area 11. In the Figures 2 to 4 example, the flap 7 is arranged on one side 10 of the frame 5 of the pressure relief panel 1. In this example, the member 13 is arranged on one side 9 of the frame 5 of the pressure relief panel 1, that is, where the face 23 ( Figure 5), and contact the surfaces 5A, 5B of the frame 5 that are respectively located in the portions 11A, 11B of the superimposed area 11 ( Figure 2 ). Alternatively, the components 13 can be arranged equally well on one side 10, where the surfaces 23 of these components contact the flap 7.

[0052] In addition, for each of the components 13, a plurality of fixing elements 14 pass through the elastomeric component 13, the frame 5, and the flap 7 and fix these various elements (the component 13, the frame 5, and the flap 7) together.

[0053] Each fixing element 14 passes through the elastomeric component 13, the frame 5, and the flap 7, respectively through the holes 19, 26, and 25 in these elements, thus allowing these elements to slide, as Figure 6 represented. Each fixing element 14 preferably corresponds to a nut and bolt assembly, as Figure 5 represented, which is formed by a bolt 15 and a nut 18. The bolt is provided with a head 16 and includes a threaded shank 17, and the nut can be screwed onto the threaded shank 17 of the bolt 15.

[0054] In a preferred embodiment, the elastomeric component 13 is an elongated component. The elongated component 13 can be produced in different ways. The elongated component 13 preferably has a straight shape, as Figures 1 to 5 represented. However, the elongated component 13 can equally well have a curved shape or a more complex shape, especially to match the shape of the opening 6 and / or the flap 7. These various shape possibilities of the component 13 give great flexibility in the production of the connection system 8 and more generally in the production of the decompression panel 1.

[0055] In the depicted embodiment, the elastomeric component 13 is a solid component provided with a plurality of holes 19 ( Figure 5 ), and these holes are intended to receive the bolts 15 of the fixing elements 14.

[0056] In a specific embodiment where the flap 7 has a rectangular shape Figures 2 to 4 , the decompression panel 1 includes a pair of identical elastomeric components 13, which are arranged along the opposite sides of the rectangular shape (in this case at the level of its short sides 7A and 7B ( Figure 4 )).

[0057] In a variant embodiment (not shown), the decompression panel can include two pairs of elastomeric components 13, where one pair is arranged at the level of its short sides 7A and 7B, and the other pair is arranged at the level of its long sides 7C and 7D.

[0058] In addition, in a preferred embodiment, the decompression panel 1 includes a metal plate 20 ( Figure 5 , Figure 6 and Figure 7). The metal plate 20 is provided with holes 21 designed to allow these fixing elements 14 to pass through. The metal plate 20 is arranged on the face 22 of the elastomeric member 13 Figure 5 ), which is opposite to the face 23 of the member 13 that contacts the faces 5A, 5B of the superposition zone 11.

[0059] This metal plate 20 enables the pressure exerted on the flap 7 and the frame 5 by all the fixing elements 14 (which fix the member 13) to be balanced. For each fixing element 14, the head 16 of the bolt 15 rests on the metal plate 20 and the nut 18 contacts the flap 7, as can be seen in Figure 6 and Figure 7 .

[0060] Furthermore, the elastomeric member 13 is provided with a housing 24 for receiving the metal plate 20. Preferably, the depth of the housing 24 is substantially equal to the thickness of the metal plate 20 and the shape is similar to the shape of the metal plate 20. In the example of Figure 5 , the metal plate 20 has a substantially rectangular shape with slightly rounded corners. This housing 24 allows the metal plate 20 to be easily positioned and held on the member 13. When the metal member 20 is received in the housing 24, the metal plate 20 is thus flush with the face 22 of the member 13, such that the metal plate 20 and the member 13 form a single block with a smooth face 22.

[0061] The operation of the pressure relief panel 1 described above will be described below with reference to Figure 6 and Figure 7 .

[0062] As indicated above, the flap 7 of the pressure relief panel 1 can assume the following two positions:

[0063] - A closed position P1 ( Figure 2 and Figure 6 ), in which the flap completely closes the opening 6; and

[0064] - At least one open position P2 ( Figure 3 , Figure 4 and Figure 7 ), in which the flap partially releases the opening 6.

[0065] In the nominal (initial) situation, the flap 7 is in the closed position P1. As shown in Figure 6 , the flap contacts the frame 5 (in particular, the portions 11A, 11B, 11C, and 11D of the superposition zone 11 surrounding the opening 6). The opening 6 in the inner wall 2 is thus completely closed and prevents any air from passing through.

[0066] The flap 7 can move from this closed position P1 to the open position P2 due to the pressure difference between the two sides 9 and 10 of the pressure relief panel 1, i.e., due to the pressure difference corresponding to the higher pressure on side 9 compared to the pressure on side 10, which is caused, for example, by the pressure relief in the pressurized area on side 10 of the inner wall 2, especially caused by rapid pressure relief.

[0067] More precisely, the pressure relief panel 1 is configured such that if the pressure difference between the two sides 9 and 10 of the pressure relief panel 1 exceeds a predetermined value, the elastomeric member 13 is compressed by the action of this pressure difference on the flap 7.

[0068] This predetermined pressure difference value depends in particular on the characteristics of the wall 2 and the characteristics of the aircraft 3. By way of example only, this predetermined value (of the pressure difference between the two sides 9 and 10 of the inner wall 2) can be approximately 40 hPa.

[0069] More precisely, in the case where the frame 5 is fixed (rigidly fastened to the wall 2), the higher pressure on side 9 Figure 7 acts in the direction depicted by the arrow F to generate a force acting on the flap 7. This force is transmitted via the fixing element 14 to the metal plate 20 and acts on the elastomeric member 13 (held by the frame 5) and compresses this elastomeric member. This compression Figure 7 generates the movement of the flap 7 in the direction depicted by the arrow G (the flap remains at a constant distance from the metal plate 20 which moves during compression), and the flap thus moves into its open position P2.

[0070] By this movement of the flap 7 relative to the fixed frame 5 in the direction of the arrow G, a passage 12 is created between the flap 7 and the frame 5 ( Figure 3 、 Figure 4 and Figure 7 ), and through this passage an air flow is generated from side 9 to side 10 (due to the pressure difference), as depicted by the arrow I in Figure 3 、 Figure 4 and Figure 7 .

[0071] This air flow enables the reduction of the pressure difference between the two sides 9 and 10 of the wall 2.

[0072] When compressed, the thickness of the member 13 changes from the value E1 ( Figure 6 ) to a value E2 that is less than the value E1 ( Figure 7 ). Thus, the passage 12 has a width ΔE (where ΔE = E1 - E2). Due to the arrangement of two identical members 13 on the corresponding opposite sides of the opening 6, this width ΔE of the passage 12 is substantially the same around the opening 6.

[0073] In a preferred embodiment, the decompression panel 1 is configured such that the air passage 12 created when the flap 7 is in the open position P2 has a total surface S2, the area A2 of which is substantially equal to the area A1 of the surface S1 of the opening 6 of the frame 5. Thus, the surface S1 having a rectangular shape with sides of lengths L1 and L2 has an area A1 that satisfies the equation A1 = L1.L2.

[0074] The area A2 of the total surface S2 of the air passage 12 corresponds to the sum of the areas of the surfaces between the frame 5 and the edges of the flap 7 in the open position P2 (i.e., the surface of the short side 7A of the flap 7 having an area substantially equal to L2.ΔE, the surface of the short side 7B of the flap 7 having an area substantially equal to L2.ΔE, the surface of the long side 7C of the flap 7 having an area substantially equal to L1.ΔE, and the surface of the long side 7D of the flap 7 having an area substantially equal to L1.ΔE). Thus, the area A2 of the total surface S2 substantially satisfies the equation A2 = 2.(L1 + L2).ΔE.

[0075] In this preferred embodiment, the compression panel 1 and in particular the one or more components 13 are configured such that the thickness difference ΔE (of the open position P2 relative to the closed position P1) enables the surface S2 to be obtained, the area A2 of which is substantially equal to the area A1 of the surface S1.

[0076] In this preferred embodiment, the decompression panel 1 thus allows substantially the same air flow to circulate (and thus substantially has the same pressure difference reduction efficacy) as if the flap 7 were completely removed and / or the opening were completely released (as is usually the case in a normal solution).

[0077] When the pressure difference (between the two sides 9 and 10 of the decompression panel 1) is again small enough, for example when the aircraft descends (and is at a higher external pressure) such that the pressure on one side 10 (which is close to the external pressure in the case of decompression of the zone located on said side 10) increases and approaches the pressure on one side 9, the elastomeric component 13 returns to its initial shape due to its inherent elastic properties, which causes the flap 7 to return to its closed position P1.

[0078] The opening 6 in the inner wall 2 is thus closed again.

[0079] Furthermore, in this closed position P1, the compression panel 1 is directly operable again.

[0080] Thus, no mechanical system or mechanism is used to move the flap 7 to the open position P2 or to subsequently return the flap to its closed position P1, in which the flap is directly operable again. Moreover, after a rapid decompression, no reset action or operation is required other than simply checking the decompression panel 1.

[0081] The decompression panel 1 also has other advantages. In particular:

[0082] - The decompression panel is low in cost;

[0083] - The decompression panel can be produced simply and quickly;

[0084] - The decompression panel allows air flow to pass through similar to a normal solution where the flap is completely removed from the opening;

[0085] - Compared with normal solutions (usually provided with complex mechanisms having multiple mechanical components), the decompression panel has fewer components; and

[0086] - The decompression panel only requires a short inspection or testing time.

Claims

1. A pressure relief panel for an aircraft, said pressure relief panel (1) comprising at least: - A frame (5), said frame being provided with an opening (6); And - A flap (7), said flap being connected to said frame (5) by a connection system (8), said flap (7) being able to adopt at least one of the following two positions: a closed position (P1) and at least one open position (P2), in said closed position, said flap completely closes said opening (6), in said at least one open position, said flap at least partially releases said opening (6), said flap (7) being adapted to move from said closed position (P1) to said open position (P2) under the action of a pressure difference between two sides (9, 10) of said pressure relief panel (1). It is characterized in that said flap (7) and said frame (5) are configured to be superimposed on at least one superimposed area (11), and said connection system (8) includes at least one elastomeric member (13), said at least one elastomeric member being arranged on one of the surfaces (5A, 5B) of said superimposed area (11) and being provided with a plurality of fixing elements (14), said fixing elements passing through said elastomeric member (13), said frame (5) and said flap (7) and fixing said elastomeric member, said frame and said flap together.

2. The decompression panel according to claim 1, wherein Said pressure relief panel (1) is configured such that if the pressure difference between two sides (9, 10) of the frame (5) of said pressure relief panel (1) exceeds a predetermined value when the pressure on the side of the frame (5) where said flap (7) is arranged is lower, then said elastomeric member (13) is compressed so as to cause said flap (7) to move away from said frame (5) and thus create an air passage (12) between said flap (7) and said frame (5).

3. The decompression panel according to claim 2, wherein Each of said fixing elements (14) passes through holes in said elastomeric member (13), said frame (5) and said flap (7) so that when said elastomeric member (13) is compressed under the action of said pressure difference, said elastomeric member, said frame and said flap can slide on said fixing element (14) and allow said flap (7) to move away from said frame (5).

4. The decompression panel according to claim 2 or 3, characterized in that, Said pressure relief panel (1) is configured such that the overall surface of the air passage (12) generated when said flap (7) is in said open position (P2) has an area that is substantially equal to the area of the surface of said opening (6) of said frame (5).

5. The decompression panel according to any one of the preceding claims, characterized in that, Said elastomeric member (13) is a solid elongated member provided with a plurality of holes (19), each of said holes being intended to receive a fixing element (14).

6. The decompression panel according to any one of the preceding claims, characterized in that, Said flap (5) has a rectangular shape, and said pressure relief panel (1) includes at least a pair of identical elastomeric members (13) arranged along opposite sides of said rectangular shape.

7. The decompression panel according to any one of the preceding claims, characterized in that, The pressure relief panel includes at least one metal plate (20), the at least one metal plate being provided with holes for the fixing elements (14) to pass through, and the metal plate (20) is arranged on a surface of the elastomeric member (13) opposite to the surface contacting the superimposed area (11).

8. The decompression panel according to claim 7, characterized in that, The elastomeric member (13) is provided with a housing (24) for receiving the metal plate (20).

9. An inner wall of an aircraft, the inner wall of the aircraft being intended to be arranged between two adjacent zones of the aircraft, characterized in that, The inner wall of the aircraft includes at least one pressure relief panel (1) according to any one of claims 1 to 8.

10. An aircraft, characterized in that, The aircraft includes at least one pressure relief panel (1) according to any one of claims 1 to 8 and / or at least one inner wall (2) of the aircraft according to claim 9.

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