Aircraft including a cargo door equipped with an improved sealing system

Abstract

The subject of the invention is an aircraft comprising a first region (42) and a second region (44), and a sealing system (54) between a door frame (52) and a door (50), the door providing access to the second region (44), the sealing system comprising: a peripheral seal (56) fastened to the door (50); a stopper (58) fastened to the door frame (52) and comprising a body (66) in the form of at least one plate extending around the periphery of the door frame (52) and parallel to the door (50) when the door (50) is in a closed position; a peripheral groove (76) positioned on the stopper (58) in such a way that when the door (50) is in a closed position, the peripheral seal (56) closes the peripheral groove (76) around the periphery of an opening (48); and at least one channel (78) configured to connect the peripheral groove (76) to the first region (42).

Description

Technical Field

[0001] The present invention relates to an aircraft comprising a cargo door equipped with an improved sealing system. Background Art

[0002] like Figure 1 As represented in FIG. 2 , the fuselage 10 of an aircraft comprises a structure formed by transverse reinforcements, called frames, and longitudinal reinforcements, called girders, and a skin 12 fixed to the structure, which separates the interior from the exterior of the fuselage.

[0003] For the rest of the description, the longitudinal direction, marked X, is parallel to the longitudinal axis A10 of the fuselage, which extends from the nose cone to the tail cone of the fuselage. A transverse plane is a plane perpendicular to the longitudinal axis A10. A longitudinal plane is a plane passing through the longitudinal axis A10.

[0004] The interior of the fuselage 10 is divided by at least one bulkhead 14 and comprises at least a first area 16 (e.g. a cabin) and at least a second area 18 (e.g. a cargo hold), which are separated by the bulkhead 14. In order to allow access to the interior of the second area 18 from the outside of the aircraft, the fuselage 10 comprises at least one opening 20 and a door 22 movable between an open position, in which the door at least partially exposes the opening 20, and a closed position, in which the door closes the opening.

[0005] The door 22 comprises a peripheral seal 24 positioned on its inner face, extending over the entire periphery of the door. According to one embodiment, the peripheral seal 24 comprises a hollow cylinder having orifices 26 which allow the interior of the hollow cylinder to communicate with the interior of the second zone 18 of the fuselage 10.

[0006] The fuselage 10 comprises a door frame 28 connected to the structure of the fuselage 10 and a stopper 30 comprising:

[0007] a body 32 in the form of a plate extending over the entire periphery of the door frame 28 towards the inside of the opening 20 and parallel to the door 22 when the door 22 is in the closed position and having a first edge 32.1 fixed to the door frame 28 and a free second edge 32.2 delimiting the opening 20,

[0008] A rib 34 , perpendicular to the body 32 , protruding towards the outside of the fuselage 10 , positioned at the level of the free second edge 32 . 2 and extending over the entire periphery of the door frame 28 .

[0009] The body 32 and the ribs 34 are positioned in such a way as to compress the peripheral seal 24 secured to the door 22 when the door is in the closed position.

[0010] The second zone 18 is equipped with a fire extinguishing system. In the event of a fire during flight, the fire extinguishing system floods the second zone 18 with a gas suitable for extinguishing the fire, such as a Halon gas. Throughout the rest of the flight, until the aircraft lands, the fire extinguishing system needs to maintain the gas concentration in the second zone 18 above a given value in order to keep the fire extinguished.

[0011] Due to the leakage of gas 36 between the peripheral seal 24 and the ribs 32, the fire extinguishing system includes an additional gas reservoir for slowly discharging the gas into the second area 18 and maintaining the gas concentration above a given value. This additional gas reservoir results in an increase in the onboard mass of the aircraft. Summary of the invention

[0012] The present invention seeks to overcome the shortcomings of the prior art.

[0013] To this end, the subject of the invention is an aircraft comprising a fuselage, a first zone and a second zone separated by a bulkhead, an opening surrounded by a door frame and configured to allow access to the second zone from the outside of the fuselage, a door movable between an open position and a closed position in which the door closes the opening, the sealing system interposed between the door frame and the door, the sealing system comprising:

[0014] - a peripheral seal fastened to the door, extending around the periphery of the door,

[0015] - a stop fastened to the door frame, comprising a body in the form of at least one plate, extending around the periphery of the door frame, parallel to the door when the door is in the closed position, having a first edge connected to the door frame and a free second edge delimiting the opening.

[0016] According to the present invention, the stopper comprises:

[0017] a peripheral groove positioned in such a way that the peripheral seal closes the peripheral groove around the periphery of the opening when the door is in the closed position,

[0018] - at least one channel configured to put said peripheral groove in communication with said first zone.

[0019] This design makes it possible to maintain the concentration of gas injected by the fire extinguishing system into the second zone in the event of an accident, thereby reducing the need for slow discharge of gas from the second zone to compensate for potential leaks. As a result, the additional gas reservoir providing slow discharge of gas is significantly reduced, thus making it possible to reduce the onboard mass.

[0020] According to another feature, the stop comprises a first rib and a second rib, the ribs being fastened to the body, projecting towards the outside of the fuselage relative to the body, extending over the entire periphery of the door frame, the ribs being spaced apart in such a way as to define, together with the body, the peripheral groove.

[0021] According to another feature, the first rib is positioned at the height level of the second edge of the body of the stopper, has a greater height than the second rib and comprises an upper portion that slopes away from the stopper towards the inside of the opening.

[0022] According to another feature, the peripheral seal includes at least one external rib protruding relative to the outer surface of the peripheral seal and configured to limit the extent to which the peripheral seal can be pushed into the peripheral groove.

[0023] According to one configuration, the outer rib of the peripheral seal is configured to bear against an upper portion of the first rib.

[0024] According to another feature, the peripheral seal comprises a hollow cylinder having at least one orifice for placing the interior of the hollow cylinder in communication with the interior of the second region of the fuselage.

[0025] According to one configuration, the opening includes an upper edge positioned in a first longitudinal plane, a lower edge positioned in a second longitudinal plane, and a first lateral edge and a second lateral edge positioned in a transverse plane; and the stop member includes two channels positioned at the height level of the first lateral edge and two channels positioned at the height level of the second lateral edge.

[0026] According to one embodiment, the stop comprises at least one plate having a first face facing the outside of the fuselage and a second face facing the inside of the fuselage, each channel being positioned in a bead provided on the second face. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Further features and advantages will become apparent from the following description of the invention, given purely by way of example with reference to the accompanying drawings, in which:

[0028] - Figure 1 This is a side view of the aircraft.

[0029] - FIG. 2 is a schematic cross-section of an aircraft door sealing system showing an embodiment of the prior art,

[0030] - FIG. 3 is a front view showing an opening formed in an aircraft fuselage according to a first embodiment of the invention,

[0031] - Figure 4 3 is a schematic cross section along IV-IV of FIG. 3 showing an aircraft door sealing system according to a first embodiment of the present invention,

[0032] - Figure 5 3 is a schematic cross section of an aircraft door sealing system according to a first embodiment of the present invention, taken along line VV of FIG. 3 ,

[0033] - Figure 6 is a perspective view of the lateral edge of the opening visible in FIG. 3 ,

[0034] - Figure 7 is a perspective view of the corner of the opening visible in FIG. 3 ,

[0035] - Figure 8 is a perspective cross section showing a stopper of a sealing system of a first embodiment of the present invention,

[0036] - Fig. 9 is a perspective view showing the air supply of an aircraft door sealing system according to a first embodiment of the present invention,

[0037] - Fig.10 is a schematic cross section of an aircraft door sealing system showing a second embodiment of the present invention, and

[0038] - Fig.11 is a schematic cross section showing an aircraft door sealing system according to a third embodiment of the present invention. DETAILED DESCRIPTION

[0039] Figures 4 to 7 A fuselage 40 of an aircraft is depicted, comprising at least a first region 42 and at least a second region 44 inside the fuselage 40 , these regions being separated by at least one bulkhead 45 .

[0040] According to one configuration, the first area 42 is a cabin where personnel are accommodated. The second area 44 is a cargo hold configured to store luggage or any other cargo.

[0041] The second area 44 is equipped with a fire extinguishing system 46 configured to inject a gas suitable for extinguishing a fire (eg, a Halon gas) into the second area 44 .

[0042] The fuselage 40 includes at least one opening 48 that allows access to the second area 44 from outside the fuselage 40 and a door 50 that is movable between an open position that at least partially exposes the opening 48 and a closed position that closes the opening 48 .

[0043] The fuselage 40 includes a door frame 52 connected to the structure of the fuselage 40 , the door frame surrounding the opening 48 , and at least one hinge configured to allow the door 50 to move between an open position and a closed position.

[0044] The fuselage 40, the first and second zones 42, 44, the bulkhead 45, the fire extinguishing system 46, the door 50, its hinges, and the door frame 52 are not further described as they may be identical to those in the prior art.

[0045] The fuselage 40 includes a sealing system 54 between the door 50 and the door frame, the sealing system comprising:

[0046] a peripheral seal 56 which is fastened to the door 50 , is positioned at the level of the inner face of the door 50 (facing the interior of the fuselage 40 ) and extends over the entire periphery of the door 50 ,

[0047] A stop 58 which delimits the opening 48 and extends over the entire periphery of the door frame 52 towards the inside of the opening 48 .

[0048] According to one embodiment, the peripheral seal 56 includes a hollow cylinder 60 and a fastening system 62 configured to couple the hollow cylinder 60 to the door 50 .

[0049] The hollow cylinder 60 has at least one aperture 64 to allow the interior of the hollow cylinder 60 to communicate with the interior of the second region 44 of the fuselage 40 .

[0050] The peripheral seal 56 is made of a material that allows it to deform elastically, more particularly to be crushed.

[0051] The stopper 58 comprises:

[0052] a body 66 in the form of at least one plate extending over the entire periphery of the door frame 52 and parallel to the door 50 when the door is in the closed position and having a first edge 66.1 connected to the door frame 52 and a free second edge 66.2 delimiting the opening 48,

[0053] A first rib 68 which is fastened to the body 66 , projects towards the outside of the fuselage 40 relative to the body 66 and extends over the entire periphery of the door frame 52 .

[0054] According to one embodiment, in order to provide a connection between the stopper 58 and the door frame 52, the stopper 58 comprises a flange 70, which is fastened to the body 66 at the height level of the first edge 66.1, firmly pressed against the door frame 52, and a plurality of fixings 72, Figure 6) provides a connection between the flange 70 and the door frame 52.

[0055] According to one feature of the invention, the stop 58 comprises a second rib 74 fastened to the body 66 , projecting towards the outside of the fuselage 40 relative to the body 66 , extending over the entire periphery of the door frame 52 and offset towards the first edge 66 . 1 relative to the first rib 68 .

[0056] The first rib 68 and the second rib 74 are spaced apart in such a manner as to define a peripheral groove 76 together with the body 66 .

[0057] The body 66 and the first and second ribs 68 and 74 are positioned in such a manner that when the door 50 is in the closed position, the peripheral seal 56 secured to the door 50 is compressed against the first and second ribs 68 and 74 and closes the peripheral groove 76 .

[0058] According to another feature of the invention, the peripheral groove 76 communicates with the first zone 42. For this purpose, the stopper 58 comprises at least one channel 78 having a first end 78.1 opening into the peripheral groove 76 and a second end 78.2 opening into the first zone 42.

[0059] In the event of an accident, instead of the gas propelled by the fire extinguishing system 46 leaking to the outside of the aircraft, the air present in the peripheral groove 76 and from the first area 42 leaks towards the outside via any leakage paths 80 that may potentially exist.

[0060] Since the first region 42 and the second region 44 are initially at the same pressure, the action of injecting gas into the second region 44 has a tendency to increase the pressure in the second region 44 and within the hollow cylinder 60 of the peripheral seal 56, thereby creating a pressure difference between the gas present in the hollow cylinder 60 and the air present in the peripheral groove 76. This pressure difference increases the pressure that presses the peripheral seal 56 firmly against the first rib 68 and the second rib 74 of the stopper 58, and this has a tendency to reduce the risk of leakage.

[0061] As shown in Figure 3 and Figure 4 As illustrated in FIG. 8 , the sealing system 54 includes at least one system for properly positioning the hollow cylinder 60 of the peripheral seal 56 relative to the first rib 68 and the second rib 74 of the stop 58 .

[0062] According to one embodiment, the door 50 includes a base plate 82 to which the peripheral seal 56 is attached and a flange 84 extending from the base plate 82 toward the interior of the fuselage, the flange 84 being configured to limit deformation of the hollow cylinder 60 of the peripheral seal 56 toward the door frame 52 .

[0063] According to one embodiment, the first rib 68 has a greater height than the second rib 74 and includes an upper portion 86 (away from the stop 58) that is inclined toward the interior of the opening 48. This inclination facilitates the positioning of the peripheral seal 56 between the first rib 68 and the second rib 74 and increases the contact area between the peripheral seal 56 and the first rib 68, which has a tendency to reduce the risk of leakage between the second area 44 and the peripheral groove 76.

[0064] When the door 50 is in the closed position, the peripheral seal 56 is immobilized between the flange 84 and the upper portion 86 of the first rib 68 .

[0065] The peripheral seal 56 includes at least one external rib 88 extending over the entire length of the seal, protruding relative to the outer surface of the peripheral seal 56, and pointing toward the middle of the opening 48. This external rib 88 is configured to bear against the upper portion 86 of the first rib 68 and limit the extent to which the peripheral seal 56 can be pushed into the peripheral groove 76.

[0066] At another point, the inclination of upper portion 86 of first rib 68 and outer rib 88 of peripheral seal 56 increases the leakage path between peripheral seal 56 and first rib 68 , and this tends to reduce the risk of leakage between second region 44 and peripheral groove 76 .

[0067] According to the configuration visible in FIG. 3 , the opening 48 comprises an upper edge 48.1 positioned in a first longitudinal plane, a lower edge 48.2 positioned in a second longitudinal plane, and a first lateral edge 48.3 and a second lateral edge 48.4 positioned in a transverse plane, the edges 48.1 to 48.4 being connected by rounded corners, as shown in FIG. Figure 7 As shown in .

[0068] According to this configuration, the sealing system 54 comprises four channels 78, two channels 78 being positioned at the level of the first lateral edge 48.3 and two other channels 78 being positioned at the level of the second lateral edge 48.4.

[0069] According to one embodiment, the stop 58 comprises at least one plate 90 comprising: a first face 90.1 facing the outside of the fuselage 40, on which the first rib 68 and the second rib 74 are provided; and a second face 90.2 facing the inside of the fuselage. This plate 90 may be planar at the level of the upper edge 48.1 and the lower edge 48.2 of the opening 48 (e.g. Figure 7 ), and is curved at the height level of the first lateral edge and the second lateral edge so as to conform to the curvature of the fuselage 40 (as shown in Figure 6 and Figure 8 ).

[0070] according to Fig. 9 In one embodiment as can be seen in FIG. 5 , each channel 78 is positioned in a bead 92 provided on the second face 90 . 2 of the plate 90 of the stop 58 .

[0071] The body 66 , the first 68 and second 74 ribs, the flange 70 , and the bead 92 may be produced in one piece and form a single component made of metal or a composite material.

[0072] According to one embodiment, the stopper 58 includes several segments positioned end to end.

[0073] according to Fig.10 In the second embodiment, which can be seen in FIG. 5 , the stop 58 has no ribs. The stop comprises a body 66 in the form of a plate 90 having, on one of its faces 90 . 1 , a peripheral groove 76 communicating with the first zone 42 , the peripheral groove being positioned in such a way that the peripheral seal 56 closes the peripheral groove 76 over the entire periphery of the opening 48 when the door 50 is in the closed position.

[0074] according to Fig.11 In the third embodiment shown in FIG. 5 , the stopper 58 comprises a single rib 94 having, at its upper edge, a peripheral groove 76 communicating with the first area 42 . The rib 94 is positioned in such a way that the peripheral seal 56 closes the peripheral groove 76 over the entire periphery of the opening 48 .

[0075] The sealing system 54 may also be installed on existing aircraft as well as on new aircraft.

[0076] In a simple and effective manner, this sealing system makes it possible to maintain the concentration of the gas injected by the fire extinguishing system 46 into the second zone 44, while reducing the need for slow discharge of gas into the second zone 44 to compensate for potential leaks. As a result, the additional gas reservoir for the slow discharge of gas is greatly reduced (if not eliminated), thus making it possible to reduce the onboard mass.

Claims

1. An aircraft, comprising a fuselage (40), a first area (42) and a second area (44) separated by a bulkhead (45) and located inside the fuselage (40), an opening (48), a door (50), and a sealing system (54), wherein the opening is surrounded by a door frame (52) and is configured to allow access to the second area (44) from outside the fuselage (40), the door being movable between an open position and a closed position, in which the door closes the opening (48), the sealing system being interposed between the door frame (52) and the door (50), the sealing system comprising: - a peripheral seal (56) fastened to the door (50) and extending around the periphery of the door (50), - a stopper (58) fastened to the door frame (52), comprising a body (66) in the form of at least one plate, extending around the periphery of the door frame (52), parallel to the door (50) when the door (50) is in the closed position, having a first edge (66.1) connected to the door frame (52) and a free second edge (66.2) delimiting the opening (48), The stop member (58) is characterized in that the stop member (58) includes: a peripheral groove (76), the peripheral groove being positioned in such a manner that when the door (50) is in the closed position, the peripheral seal (56) closes the peripheral groove (76) around the periphery of the opening (48); and at least one channel (78), the at least one channel being configured to connect the peripheral groove (76) to the first area (42).

2. The aircraft according to claim 1, characterized in that The stopper (58) includes a first rib (68) and a second rib (74), the first rib and the second rib being fastened to the body (66), projecting toward the outside of the fuselage (40) relative to the body (66), extending over the entire periphery of the door frame (52), the first rib and the second rib being spaced apart in such a manner that they can define the peripheral groove (76) together with the body (66).

3. The aircraft according to claim 2, characterized in that: The first rib (68) is positioned at the height level of the second edge (66.2) of the body (66) of the stopper (58), has a greater height than the second rib (74), and includes an upper portion (86) which is inclined away from the stopper (58) towards the inside of the opening (48).

4. The aircraft according to any one of claims 1 to 3, characterized in that The peripheral seal (56) includes at least one external rib (88) that projects relative to an outer surface of the peripheral seal (56) and is configured to limit the extent to which the peripheral seal (56) can be pushed into the peripheral groove (76).

5. The aircraft according to claim 3, characterized in that: The peripheral seal (56) includes at least one external rib (88) that protrudes relative to the outer surface of the peripheral seal (56) and is configured to limit the extent to which the peripheral seal (56) can be pushed into the peripheral groove (76), and the external rib (88) of the peripheral seal (56) is configured to bear against an upper portion (86) of the first rib (68).

6. The aircraft according to any one of claims 1 to 3 and 5, characterized in that: The peripheral seal (56) includes a hollow cylinder (60) having at least one orifice (64) to allow the interior of the hollow cylinder (60) to communicate with the interior of the second region (44) of the fuselage (40).

7. The aircraft according to claim 4, characterized in that: The peripheral seal (56) includes a hollow cylinder (60) having at least one orifice (64) to allow the interior of the hollow cylinder (60) to communicate with the interior of the second region (44) of the fuselage (40).

8. The aircraft according to any one of claims 1 to 3 and 5, characterized in that: The opening (48) comprises an upper edge (48.1) positioned in a first longitudinal plane, a lower edge (48.2) positioned in a second longitudinal plane, and a first lateral edge (48.3) and a second lateral edge (48.4) positioned in a transverse plane, and is characterized in that the stop (58) comprises two channels (78) positioned at the height level of the first lateral edge (48.3) and two channels (78) positioned at the height level of the second lateral edge (48.4).

9. The aircraft according to claim 4, characterized in that: The opening (48) comprises an upper edge (48.1) positioned in a first longitudinal plane, a lower edge (48.2) positioned in a second longitudinal plane, and a first lateral edge (48.3) and a second lateral edge (48.4) positioned in a transverse plane, and is characterized in that the stop (58) comprises two channels (78) positioned at the height level of the first lateral edge (48.3) and two channels (78) positioned at the height level of the second lateral edge (48.4).

10. The aircraft according to claim 6, characterized in that: The opening (48) comprises an upper edge (48.1) positioned in a first longitudinal plane, a lower edge (48.2) positioned in a second longitudinal plane, and a first lateral edge (48.3) and a second lateral edge (48.4) positioned in a transverse plane, and is characterized in that the stop (58) comprises two channels (78) positioned at the height level of the first lateral edge (48.3) and two channels (78) positioned at the height level of the second lateral edge (48.4).

11. The aircraft according to claim 7, characterized in that: The opening (48) comprises an upper edge (48.1) positioned in a first longitudinal plane, a lower edge (48.2) positioned in a second longitudinal plane, and a first lateral edge (48.3) and a second lateral edge (48.4) positioned in a transverse plane, and is characterized in that the stop (58) comprises two channels (78) positioned at the height level of the first lateral edge (48.3) and two channels (78) positioned at the height level of the second lateral edge (48.4).

12. The aircraft according to any one of claims 1 to 3 and 5, characterized in that: The stopper (58) comprises at least one plate (90) having a first face (90.1) facing the exterior of the fuselage (30) and a second face (90.2) facing the interior of the fuselage, each channel (78) being positioned in a bead (92) provided on the second face (90.2).

13. The aircraft according to claim 4, characterized in that The stopper (58) comprises at least one plate (90) having a first face (90.1) facing the exterior of the fuselage (30) and a second face (90.2) facing the interior of the fuselage, each channel (78) being positioned in a bead (92) provided on the second face (90.2).

14. The aircraft according to claim 6, characterized in that The stopper (58) comprises at least one plate (90) having a first face (90.1) facing the exterior of the fuselage (30) and a second face (90.2) facing the interior of the fuselage, each channel (78) being positioned in a bead (92) provided on the second face (90.2).

15. The aircraft according to claim 7, characterized in that The stopper (58) comprises at least one plate (90) having a first face (90.1) facing the exterior of the fuselage (30) and a second face (90.2) facing the interior of the fuselage, each channel (78) being positioned in a bead (92) provided on the second face (90.2).

16. The aircraft according to claim 8, characterized in that The stopper (58) comprises at least one plate (90) having a first face (90.1) facing the exterior of the fuselage (30) and a second face (90.2) facing the interior of the fuselage, each channel (78) being positioned in a bead (92) provided on the second face (90.2).

17. The aircraft according to claim 9, characterized in that The stopper (58) comprises at least one plate (90) having a first face (90.1) facing the exterior of the fuselage (30) and a second face (90.2) facing the interior of the fuselage, each channel (78) being positioned in a bead (92) provided on the second face (90.2).

18. The aircraft according to claim 10, characterized in that The stopper (58) comprises at least one plate (90) having a first face (90.1) facing the exterior of the fuselage (30) and a second face (90.2) facing the interior of the fuselage, each channel (78) being positioned in a bead (92) provided on the second face (90.2).

19. The aircraft according to claim 11, characterized in that: The stopper (58) comprises at least one plate (90) having a first face (90.1) facing the exterior of the fuselage (30) and a second face (90.2) facing the interior of the fuselage, each channel (78) being positioned in a bead (92) provided on the second face (90.2).

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