Portion of aircraft including a depressurization-protected equipment door

Abstract

Aircraft portion comprising a depressurization-safe equipment door. The aircraft portion comprises equipment including: - an outer wall delimiting an enclosure; - a door facing an aisle and movable between a closed and an open configuration; wherein the aisle has: - a maximum width when the door is in the closed configuration; - a minimum width when the door is in the open configuration; and wherein, when the door is in the closed configuration, and in the event of depressurization, the door is moved and maintained in an emergency configuration in which the aisle has an optimal width that is sufficient to simultaneously: - allow air to escape from the enclosure; and - allow passengers to use the aisle and pass in front of the equipment. Figure for abbreviation: Figure 4

Description

Title of the invention: Portion of an aircraft comprising a depressurization-protected equipment door

[0001] The present invention relates to an aircraft portion comprising:

[0002] - a fuselage delimiting an aircraft cabin;

[0003] - a delimiting device, with other equipment or with a wall of the portion of aircraft, an aisle extending along an aisle axis, the aisle having a width measured along a transverse axis substantially perpendicular to the aisle axis, the equipment comprising:

[0004] - an outer wall delimiting an enclosure;

[0005] - a door facing the driveway and comprising at least one first leaf and at minus a second leaf, each of the at least one first leaf and the at least one second leaf being rotatably mounted on the outer wall respectively along a first axis of rotation and a second axis of rotation, the door being able to be moved between:

[0006] - a closed configuration in which at least one first leaf and the other minus a second gate prevent access to the enclosure by both extending in a plane substantially parallel to the aisle axis and to a vertical axis substantially perpendicular to the aisle axis and to the transverse axis;

[0007] - an open configuration in which at least one first leaf and at least a second leaf extends at least partially into the alley to provide access to the enclosure;

[0008] in which, near the door, the alley has:

[0009] - a maximum width when the door is in the closed configuration;

[0010] - a minimum width when the door is in the open configuration.

[0011] In such a section of the aircraft, in the event of depressurization (i.e., loss of cabin pressurization), the air trapped within the equipment enclosure (for example, a lavatory) must be evacuated, particularly when the enclosure represents a significant volume of air. Evacuating the air from inside the enclosure prevents the outer wall from bursting and fragments of the outer wall and / or door from being scattered.

[0012] When the door is in the closed position, and particularly when the door is locked in the closed position, the air contained within the enclosure cannot escape. If the pressure difference is sufficiently high, this can cause the lock to break and the door to move into the open position. This situation is unsatisfactory because, in the open position, the door extends to crosses the aisle and obstructs it. This can hinder passenger evacuation through the aisle.

[0013] There is therefore a need for a door system which improves passenger safety, particularly in the event of depressurization.

[0014] An objective of the invention is, therefore, to provide a portion of an aircraft which improves passenger safety, particularly in the event of depressurization.

[0015] To this end, the invention relates to a portion of an aircraft comprising:

[0016] - a fuselage delimiting an aircraft cabin;

[0017] - a delimiting device, with other equipment or with a wall of the portion of aircraft, an aisle extending along an aisle axis, the aisle having a width measured along a transverse axis substantially perpendicular to the aisle axis, the equipment comprising:

[0018] - an outer wall delimiting an enclosure;

[0019] - a door facing the driveway and comprising at least one first leaf and at minus a second leaf, each of the at least one first leaf and the at least one second leaf being rotatably mounted on the outer wall respectively along a first axis of rotation and a second axis of rotation, the door being able to be moved between:

[0020] - a closed configuration in which at least one first leaf and the other minus a second gate prevent access to the enclosure by both extending in a plane substantially parallel to the aisle axis and to a vertical axis substantially perpendicular to the aisle axis and to the transverse axis;

[0021] - an open configuration in which at least one first leaf and at least a second leaf extends at least partially into the alley to provide access to the enclosure;

[0022] in which, near the door, the alley has:

[0023] - a maximum width when the door is in the closed configuration;

[0024] - a minimum width when the door is in the open configuration; and

[0025] in which, when the door is in the closed configuration, and in the event of During depressurization, the door is moved and held in an emergency configuration between the closed and open configurations, in which, near the door, the aisle has an optimal width between the maximum and minimum widths and is sufficient to simultaneously:

[0026] - to allow air to escape from the enclosure; and

[0027] - allow passengers to use the aisle and pass in front of the equipment.

[0028] Thanks to the invention, when the door is in the closed configuration, and in the event of depressurization, the door is opened sufficiently to allow the air trapped inside the equipment enclosure to escape while encroaching as little as possible on the aisle. This helps to balance the pressure between the inside and outside of the enclosure while minimizing disruption to passenger evacuation via the aisle.

[0029] The aircraft portion according to the invention may comprise one or more of the following features, considered alone or in any technically feasible combination:

[0030] - the equipment further includes a locking system comprising a strike plate mounted on at least one of the first leaves and a deadbolt mounted on at least one of the second leaves,

[0031] wherein the deadbolt is movable in translation along a locking axis, which is substantially parallel to the aisle axis when the door is in the closed configuration, between:

[0032] - a locking position in which, when the door is in the configuration When closed, the deadbolt cooperates with the strike plate to hold the door in the closed position;

[0033] - an unlocking position in which, when the door is in the In the closed configuration, the deadbolt is positioned away from the strike plate to allow the door to move from the closed configuration to the open configuration;

[0034] the deadbolt comprising:

[0035] - a first part intended to extend inside the strike plate in the position of lockdown ;

[0036] - a second part mounted on at least a second clapper; and

[0037] - an articulation mechanism connecting the first part and the second part of the bolt fixed and extending between at least one first leaf and at least one second leaf when the door is in the closed configuration, the articulation mechanism comprising a joint allowing the movement of the first part relative to the second part along an axis of rotation substantially parallel to the vertical axis;

[0038] in which, when the door is in the closed configuration, when the deadbolt is in the locked position, and in the event of depressurization, the door is moved into the emergency configuration by the rotation of the first part of the deadbolt relative to the second part of the deadbolt around the axis of rotation of the hinge;

[0039] - the joint is a pin joint comprising a pin extending approximately parallel to the vertical axis;

[0040] - the articulation mechanism further includes a mechanical fuse designed to:

[0041] - prevent the rotation of the first part of the deadbolt relative to the second part of the deadbolt via the joint, under normal flight conditions;

[0042] - to rupture in the event of depressurization, the rupture of the mechanical fuse allowing the rotation of the first part of the deadbolt relative to the second part of the deadbolt via the joint;

[0043] - in the event of depressurization, the mechanical fuse is designed to break under a pressure force greater than or equal to a force threshold,

[0044] in which the force threshold is less than or equal to the force generated by the depressurization on the door, and in which the mechanical fuse is designed to remain intact under forces below the force threshold;

[0045] - the force threshold is between 550 N and 750 N;

[0046] - the mechanical fuse is a fusible pin extending substantially parallel to the axis of rotation of the joint, and in which, in the event of depressurization, the fusible pin breaks under the effect of a shear stress;

[0047] - a shear stress threshold corresponding to the force threshold is included between 250 MPa and 500 MPa;

[0048] - the fusible pin and the joint are separated, in a substantially perpendicular to the axis of rotation of the joint, by a distance between 10 mm and 15 mm;

[0049] - the fusible shaft is formed from an aluminum alloy, and in which the pin fuse has a diameter between 0.125 inch and 0.5 inch;

[0050] - the articulation mechanism further comprises a stop and a stop complementary designed to cooperate in order to limit the rotation of the first part of the deadbolt relative to the second part of the deadbolt, via the articulation, to a maximum rotation in which the door is in the emergency configuration;

[0051] - the strike plate includes a housing intended to receive the first part of the bolt dormant in the locked position, the deadbolt comprising at least one bearing designed to cooperate with internal walls of the housing during the movement of the deadbolt between the locked and unlocked positions to guide the movement of the deadbolt;

[0052] - at least one bearing is a ball bearing;

[0053] - the deadbolt comprises at least two bearings arranged side by side along the locking axis;

[0054] - the aircraft portion is such that:

[0055] - the minimum width of the aisle near the door is between 4 inches and 8 inches;

[0056] - the optimal width of the aisle near the door is between 15 inches and 25 inches;

[0057] - the aircraft portion is such that:

[0058] - in the open configuration of the door, each of the at least one first leaf and at least one second leaf forms an angle between 75° and 100° with the aisle axis;

[0059] - in the emergency configuration of the door, each of the at least one first one leaf and at least one second leaf forms an angle between 5° and 15° with the axis of the driveway;

[0060] - the aircraft cabin extends along a longitudinal axis of the aircraft, the equipment being arranged in a lateral part of the aircraft cabin, the aisle axis being substantially parallel to the longitudinal axis of the aircraft;

[0061] - the equipment is an aircraft toilet;

[0062] - the equipment delimits the aisle with a partition wall separating it from the aircraft portion, the separation wall extending substantially perpendicularly to the aisle axis in a perpendicular plane, the separation wall of the aircraft portion comprising an edge delimiting the aisle with the equipment,

[0063] in which the first axis of rotation or the second axis of rotation of the leaves extends in the perpendicular plane,

[0064] in which the aisle has a passage width corresponding to the minimum distance between:

[0065] - the edge of the separating wall; and

[0066] - at least one first leaf or at least one second leaf;

[0067] the span of passage being:

[0068] - between 4 inches and 8 inches in the open door configuration;

[0069] - between 18 inches and 22 inches in the emergency door configuration.

[0070] The invention also relates to an aircraft comprising an aircraft portion as described above.

[0071] The invention will be better understood upon reading the following description, provided solely by way of example, and made with reference to the accompanying drawings, in which:

[0072] [Fig-1] The [Fig.1] is a schematic illustration of an aircraft according to the invention;

[0073] [Fig.2] Fig.2 is a top view of a portion of an aircraft according to the invention and being part of the aircraft in [Fig.1], the door being in the closed configuration;

[0074] [Fig.3] [Fig.3] is a schematic illustration of a top view of the aircraft portion of [Fig.2], with the door in the open configuration;

[0075] [Fig. 4] Fig. 4 is a schematic illustration of a top view of the portion aircraft of the [Fig.2], the door being in the emergency configuration;

[0076] [Fig. 5] Fig. 5 is a schematic illustration of a side view of a system of locking of the equipment of the aircraft portion of [Fig.2];

[0077] [Fig. 6] Fig. 6 is a schematic illustration of a cross-section of the locking system of the [Fig. 5] according to section plane VLVI, the door being in the closed configuration and the deadbolt of the locking system being in the locked position;

[0078] [Fig.7] Fig.7 is a schematic illustration of a cross-section of the locking system of [Fig. 5] according to the same cross-sectional plane as for [Fig. 6], the door being in the emergency configuration; and

[0079] [Fig.8] The [Fig.8] is a schematic illustration of a top view of a portion of the aircraft according to the invention and forming part of the aircraft of the [Fig.1], in which the door is in the open configuration and in which the aisle is delimited by the equipment and a partition wall of the portion of the aircraft.

[0080] Fig. 1 shows an aircraft 1 according to the invention.

[0081] Figures 2 to 8 show a portion 10 of the aircraft 1 according to the invention.

[0082] The aircraft portion 10 comprises a fuselage 12, equipment 20 and other equipment 88. In what follows, equipment 20 will be referred to as the first equipment 20 and other equipment 88 will be referred to as the second equipment 88.

[0083] The fuselage 12 delimits an aircraft cabin 14.

[0084] Advantageously, the aircraft cabin 14 extends along a longitudinal axis X-X' of the aircraft 1.

[0085] The first equipment 20 delimits, with the second equipment 88 or with a wall 16 of the aircraft portion 10, an aisle 36 extending along an aisle axis A-A'.

[0086] For example, the first piece of equipment 20 is an aircraft toilet. Advantageously, the aircraft toilet comprises, within an enclosure 24 of the first piece of equipment 20, a toilet and / or a washbasin and / or any other furniture conventionally used in an aircraft toilet.

[0087] The first equipment 20 comprises an outer wall 22 and a door 28.

[0088] Advantageously, the first equipment 20 further includes a locking system 40.

[0089] Advantageously still, the first equipment 20 is arranged in a lateral part 15 of the aircraft cabin 14, for example against the fuselage 12 of the aircraft portion 10.

[0090] The outer wall 22 delimits the enclosure 24.

[0091] Door 28 is opposite aisle 36.

[0092] The door 28 comprises at least a first leaf 30 and at least a second leaf 32. In what follows, a door 28 comprising a single first leaf 30 and a single second leaf 32 is described. Of course, the invention also relates to aircraft portions 10 in which the door 28 has several first leaves 30 and / or several second leaves 32.

[0093] Door 28 can be moved between:

[0094] - a closed configuration ([Fig.2]) in which the first leaf 30 and the second gate 32 prevent access to enclosure 24 by extending both in a plane DP substantially parallel to the aisle axis A-A' and to a vertical axis Z-Z' substantially perpendicular to the aisle axis A-A' and to a transverse axis Y-Y' (which is also substantially perpendicular to the aisle axis A-A');

[0095] - an open configuration (Figures 3 and 8) in which the first leaf 30 and the second gate 32 extend at least partially into the aisle 36 to give access to enclosure 24.

[0096] The door 28 is also movable in an emergency configuration ([Fig.4], and also represented in dotted lines on [Fig.8]) between the closed configuration and the open configuration.

[0097] In particular, when the door 28 is in the closed configuration, and in the event of depressurization, the door 28 is moved, in particular from the closed configuration to the emergency configuration, and maintained in the emergency configuration.

[0098] Advantageously, in the closed configuration, the door 28 and the outer wall 22 are substantially airtight, so that substantially no air escapes from the enclosure 24 through the door 28 and / or the outer wall 22.

[0099] The first leaf 30 is rotatably mounted on the outer wall 22 along a first axis of rotation RI, which is notably substantially parallel to the vertical axis Z-Z'.

[0100] The second leaf 32 is rotatably mounted on the outer wall 22 about a second axis of rotation R2, advantageously substantially parallel to the first axis of rotation RL

[0101] For example, the first axis of rotation RI and the second axis of rotation R2 extend substantially in the plane DP.

[0102] For example, in the open configuration of the door 28 ([Fig.3]), the first leaf 30 and the second leaf 32 each form an angle Al between 75° and 100°, in particular substantially equal to 90°, with the aisle axis A-A'.

[0103] For example, in the emergency configuration of door 28 ([Fig.4]), each of the first leaf 30 and the second leaf 32 forms an angle A2 between 5° and 15°, in particular substantially equal to 11°, with the aisle axis A-A'.

[0104] For example, the first axis of rotation RI and the second axis of rotation R2 are separated by a distance DI measured along the aisle axis A-A', between 25 inches and 35 inches, preferably substantially equal to 30 inches.

[0105] The aisle 36 has a width W measured along the transverse axis Y-Y' substantially perpendicular to the aisle axis A-A'.

[0106] Advantageously, the aisle axis A-A' is substantially parallel to the longitudinal axis X-X' of aircraft 1.

[0107] Near gate 28, aisle 36 has:

[0108] - a maximum width WMAX when the door 28 is in the closed configuration ([Fig.2]);

[0109] - a minimum width WMIN when door 28 is in the open configuration ([Fig.3]); and

[0110] - an optimal WOPT width when door 28 is in the emergency configuration ([Fig.4]).

[0111] The optimal width WOPT is between the maximum width WMAX and the minimum width WMIN and corresponds to a width W sufficient to simultaneously:

[0112] - to allow air to escape from enclosure 24; and

[0113] - allow passengers to use aisle 36 and pass in front of the first equipment 20.

[0114] For example, the minimum width WMIN of aisle 36 near door 28 is between 4 inches and 8 inches.

[0115] For example, the optimal WOPT width of aisle 36 near door 28 is between 15 inches and 25 inches.

[0116] The locking system 40 includes a strike plate 42 and a deadbolt 50.

[0117] Advantageously, as illustrated in [Fig.5], the locking system 40 further includes a wheel 82.

[0118] The strike plate 42 is mounted on the first leaf 30.

[0119] Advantageously, the strike plate 42 includes a housing 44.

[0120] Housing 44 is intended to receive a first part 52 of the deadbolt 50 in a deadbolt locking position 50.

[0121] The deadbolt 50 is mounted on the second leaf 32.

[0122] With reference to [Fig.5], the deadbolt 50 is movable in translation along a locking axis B-B' between the locking position (illustrated in Figures 2, 5 and 6) and an unlocking position ([Fig.3]).

[0123] Advantageously, the locking axis B-B' is substantially parallel to the aisle axis A-A' when the door 28 is in the closed configuration, as illustrated in [Fig.2],

[0124] When the door 28 is in the closed configuration and the deadbolt 50 is in the locked position (Figures 2, 5 and 6), the deadbolt 50 cooperates with the strike plate 42 to keep the door 28 in the closed configuration, in particular by simultaneously preventing the rotation of the first leaf 30 around the first axis of rotation RI and of the second leaf 32 around the second axis of rotation R2.

[0125] When the door 28 is in the closed configuration and the deadbolt 50 is in the unlocked position, the deadbolt 50 is moved away from the strike plate 42 so as to allow door 28 to move from the closed configuration to the open configuration.

[0126] Advantageously, as illustrated in [Fig.5], the deadbolt 50 further comprises a rack surface 58.

[0127] With reference to figures 5 to 7, the deadbolt 50 comprises a first part 52, a second part 54 and a hinge mechanism 62.

[0128] The first part 52 is intended to extend inside the strike plate 42, in particular inside the housing 44, in the locked position.

[0129] The second part 54 is mounted on the second clapper 32.

[0130] Advantageously, the deadbolt 50 includes at least one bearing 56 designed to cooperate with the inner walls 45 of the housing 44 of the strike plate 42 during the movement of the deadbolt 50 between the locking and unlocking positions to guide the movement of the deadbolt 50, in particular of the first part 52 of the deadbolt 50.

[0131] In particular, the deadbolt 50 comprises at least two bearings 56 (for example exactly two bearings 56 in the example of figures 5 to 7) arranged side by side along the locking axis B-B'.

[0132] Advantageously, at least one bearing 56 is a ball bearing.

[0133] Advantageously, at least one bearing 56 is designed to cooperate with the inner walls 45 of the housing 44 of the strike plate 42 when the door 28 is moved from the closed configuration to the emergency configuration. As illustrated in [Fig. 7], when the door 28 has been moved from the closed configuration to the emergency configuration, the first portion 52 of the deadbolt 50 has moved at least partially out of the housing 44 of the strike plate 42, but includes at least a portion remaining in said housing 44. In particular, the portion of the first portion 52 of the deadbolt 50 remaining in the housing 44 carries at least one bearing 56.

[0134] For example, as illustrated in [Fig.5], the first part 52 and / or the second part 54 carries the rack surface 58.

[0135] The articulation mechanism 62 connects the first part 52 and the second part 54 of the deadbolt 50.

[0136] The hinge mechanism 62 extends between the first leaf 30 and the second leaf 32 when the door 28 is in the closed configuration, and in particular when the door 28 is in the emergency configuration.

[0137] Advantageously, when the door 28 is in the closed configuration, the first part 52, the hinge mechanism 62 and the second part 54 are successively arranged in line along the locking axis B-B'.

[0138] The articulation mechanism 62 includes a joint 64.

[0139] Advantageously, the articulation mechanism 62 further includes a mechanical fuse 68.

[0140] Advantageously, the articulation mechanism 62 further includes a stop 74 and a complementary stop 76.

[0141] The joint 64 allows the movement of the first part 52 of the deadbolt 50 relative to the second part 54 of the deadbolt 50 around an axis of rotation R3 substantially parallel to the vertical axis Z-Z'.

[0142] When the door 28 is in the closed configuration, when the deadbolt 50 is in the locked position, and in the event of depressurization, the door 28 is moved into the emergency configuration by the rotation of the first part 52 of the deadbolt 50 relative to the second part 54 of the deadbolt 50 around the axis of rotation R3 (as illustrated in [Fig.7]).

[0143] Advantageously, the joint 64 is a pin joint comprising a pin 66 extending substantially parallel to the vertical axis Z-Z', in particular through the first part 52 and the second part 54 of the deadbolt 50.

[0144] The mechanical fuse 68 is designed to:

[0145] - prevent the rotation of the first part 52 of the deadbolt 50 relative to the second part 54 of the deadbolt 50 via the joint 64 under normal flight conditions (in particular under normal cabin pressurization, in which the pressure difference between the enclosure 24 and the aisle 36 is small);

[0146] - to rupture in the event of depressurization, the rupture of the mechanical fuse 68 allowing The rotation of the first part 52 of the deadbolt 50 relative to the second part 54 of the deadbolt 50 via the hinge 64. The rotation of the first part 52 of the deadbolt 50 relative to the second part 54 of the deadbolt 50 via the hinge 64 allows the rotation of the first leaf 30 relative to the first axis of rotation RI and of the second leaf 32 relative to the second axis of rotation R2, at least until the door reaches the emergency configuration.

[0147] In particular, in the event of depressurization, the mechanical fuse 68 is designed to break under a pressure force greater than or equal to a force threshold.

[0148] Advantageously, the force threshold is less than or equal to the force generated by the depressurization on the gate 28.

[0149] Advantageously still, the mechanical fuse 68 is designed to remain intact under forces below the force threshold.

[0150] In particular, the force threshold is chosen so that the typical forces that may be applied to the door 28 under normal flight conditions do not lead to the rupture of the mechanical fuse 68. For example, the force threshold is chosen so that that the force generated by a passenger leaning on door 28 or pushing door 28 when door 28 is in the closed configuration and deadbolt 50 is in the locked position, does not cause the mechanical fuse 68 to break.

[0151] For example, the force threshold is between 550 N and 750 N, for example substantially equal to 668.5 N.

[0152] Advantageously, the mechanical fuse 68 is a fusible pin 70 extending substantially parallel to the axis of rotation R3 of the joint 64. In particular, the fusible pin 70 and the pin 66 of the joint 64 are substantially parallel. Advantageously, the fusible pin 70 and the pin 66 extend in a plane substantially perpendicular to the aisle axis A-A'.

[0153] Advantageously still, the fusible pin 70 extends through the first part 52 and the second part 54 of the deadbolt 50.

[0154] In the event of depressurization, the fusible pin 70 breaks under the effect of a shear stress. In particular, said shear stress arises from the rotational stress applied to the hinge 64 by the pressure force applied to the door 28 and to the deadbolt 50 under the effect of the depressurization.

[0155] For example, a shear stress threshold corresponding to the force threshold is between 250 MPa and 500 MPa, for example substantially equal to 341.4 MPa.

[0156] For example, as illustrated in [Fig.6], in a plane PI substantially perpendicular to the axis of rotation R3 of the joint 64, the fusible pin 70 and the joint 64 (in particular the pin 66 of the joint 64) are separated by a distance D2 of between 10 mm and 15 mm, for example substantially equal to 12 mm.

[0157] Advantageously, the fusible pin 70 is formed from an aluminum alloy.

[0158] Advantageously still, the fusible pin 70 has a diameter between 0.125 inch and 0.5 inch, for example substantially equal to 0.138 inch.

[0159] The stop 74 and the complementary stop 76 of the hinge mechanism 62 are designed to cooperate in order to limit the rotation of the first part 52 of the deadbolt 50 relative to the second part 54 of the deadbolt 50, via the hinge 64, to a maximum rotation (illustrated in [Fig.7]) in which the door 28 is in the emergency configuration.

[0160] In particular, the cooperation of the stop 74 and the complementary stop 76 prevents the door 28 from moving from the emergency configuration to the open configuration.

[0161] In the example of figures 6 and 7, the stop 74 is defined by the first part 52 of the deadbolt 50 and the additional stop 76 is defined by the second part 54 of the deadbolt 50.

[0162] In particular, the stop 74 and the complementary stop 76 are each of the surfaces 78 extending in planes which include the axis of rotation R3 of the joint 64.

[0163] When the door 28 is in the closed configuration, the planes of the surfaces 78 are separated by an angle B ([Fig.6]) which corresponds to the maximum rotation angle of the first part 52 of the deadbolt 50 relative to the second part 54 of the deadbolt 50.

[0164] Advantageously, when the door 28 is in the emergency configuration, the cooperation of the stop 74 with the complementary stop 76 and the extension of the first part 52 of the deadbolt 50 inside the housing 44 of the strike plate 42 prevent the door 28 from moving further towards the open configuration.

[0165] With reference to [Fig.5], the wheel 82 of the locking system 40 includes a pinion surface 84 designed to cooperate with the rack surface 58 of the deadbolt 50 in order to move the deadbolt 50 between the locking position and the unlocking position.

[0166] In particular, the knob 82 is designed to be turned by a user, in particular a user standing in the aisle 36, in order to move the deadbolt 50 between the locked and unlocked positions. For example, where the enclosure 24 is designed to accommodate passengers, in particular where the first piece of equipment 20 is a toilet cubicle, the first piece of equipment 20 includes another locking system (not shown) designed to be used by a user standing in the enclosure 24 to lock or unlock the door 28.

[0167] The second piece of equipment 88 is for example a piece of furniture arranged inside the aircraft cabin 14, a storage room, a berth, etc.

[0168] In the example of [Fig.8], the first piece of equipment 20 delimits the aisle 36 with a separation wall 17 (which is a wall 16) from the aircraft portion 10.

[0169] The separation wall 17 of the aircraft portion 10 extends substantially perpendicularly to the aisle axis A-A', in particular to the longitudinal axis X-X' of the aircraft 1, in a plane perpendicular P3.

[0170] The separation wall 17 of the aircraft portion 10 includes an edge 18 delimiting the aisle 36 with the first equipment 20.

[0171] For example, as illustrated in [Fig.8], the first axis of rotation RI or the second axis of rotation R2 of the leaves 30, 32 extends in the perpendicular plane P3. In the specific example of [Fig.8], the first axis of rotation RI extends in the perpendicular plane P3.

[0172] For example, aisle 36 has a passage width PS which corresponds to the minimum distance between:

[0173] - the edge 18 of the separating wall 17; and

[0174] - the first clapper 30 or the second clapper 32.

[0175] For example, the PS passage span is:

[0176] - between 4 inches and 8 inches, in particular substantially equal to 6 inches, in the open configuration of door 28 (in solid lines in [Fig. 8]); and

[0177] - between 18 inches and 22 inches, in particular substantially equal to 20 inches, in the emergency configuration of door 28 (dotted line in [Fig.8]).

[0178] In the example of [Fig.8], the width W of the aisle 36 is measured in the perpendicular plane P3 from a projection of the door leaves 30, 32 onto the perpendicular plane P3. In other words, in the example of [Fig.8], the width W of the aisle 36 is the smallest distance in the perpendicular plane P3 between the edge 18 of the partition wall 17 and the projection of the door leaves 30, 32 onto the perpendicular plane P3.

[0179] Thanks to the invention, when the door 28 is in the closed configuration, and in the event of depressurization, the door 28 opens, under the pressure force generated by the depressurization, sufficiently to let the air trapped in the enclosure 24 of the first equipment 20 escape while encroaching as little as possible on the aisle 36.

[0180] In particular, the locking system 40 of the first equipment 20, in particular the hinge mechanism 62, allows the door 28 to switch from the closed configuration to the emergency configuration in the event of depressurization.

[0181] This makes it possible to balance the pressure between the inside and outside of the enclosure 24 while allowing passengers to efficiently evacuate the cabin 14 by using the aisle 36 and passing in front of the first piece of equipment 20.

Claims

1. Demands Portion of an aircraft (10) of an aircraft (1), comprising: - a fuselage (12) delimiting an aircraft cabin (14); - a piece of equipment (20) delimiting, with another piece of equipment (88) or with a wall (16, 17) of the aircraft portion (10), an aisle (36) extending along an aisle axis (A-A'), the aisle (36) having a width (W) measured along a transverse axis (Y-Y') substantially perpendicular to the aisle axis (A-A'), the equipment (20) comprising: - an outer wall (22) delimiting an enclosure (24); - a door (28) facing the aisle (A-A') and comprising at least one first leaf (30) and at least one second leaf (32), each of the at least one first leaf (30) and the at least one second leaf (32) being rotatably mounted on the outer wall (22) respectively along a first axis of rotation (RI) and a second axis of rotation (R2), the door (28) being able to be moved between: - a closed configuration in which at least one first leaf (30) and at least one second leaf (32) prevent access to the enclosure (24) by both extending in a plane (DP) substantially parallel to the aisle axis (A-A') and to a vertical axis (Z-Z') substantially perpendicular to the aisle axis (A-A') and to the transverse axis (Y-Y'); - an open configuration in which at least one first leaf (30) and at least one second leaf (32) extend at least partially into the aisle (36) to give access to the enclosure (24); in which, near the gate (28), the alley (36) has: - a maximum width (WMAX) when the door (28) is in the closed configuration; - a minimum width (WMIN) when the door (28) is in the open configuration; and wherein, when the door (28) is in the closed configuration, and in the event of depressurization, the door (28) is moved and maintained in an emergency configuration between the closed and open configurations, wherein, in the vicinity of the door (28), the aisle has an optimal width (WOPT) between the maximum width (WMAX) and the minimum width (WMIN) and corresponding to a width sufficient to simultaneously: - allow air to escape from the enclosure (24); and - allow passengers to use the aisle (36) and pass in front of the equipment (20).

2. Portion of aircraft (10) according to claim 1, wherein the equipment (20) further comprises a locking system (40) including a strike plate (42) mounted on at least one first leaf (30) and a deadbolt (50) mounted on at least one second leaf (32), wherein the deadbolt (50) is movable in translation along a locking axis (B-B'), which is substantially parallel to the aisle axis (A-A') when the door (28) is in the closed configuration, between: - a locking position in which, when the door (28) is in the closed configuration, the deadbolt (50) cooperates with the strike plate (42) to hold the door (28) in the closed configuration; - an unlocking position in which, when the door (28) is in the closed configuration, the deadbolt (50) is moved away from the strike plate (42) so as to allow movement of the door (28) from the closed configuration to the open configuration;the deadbolt (50) comprising: - a first part (52) intended to extend inside the strike plate (42) in the locked position; - a second part (54) mounted on at least one second leaf (32); and - a hinge mechanism (62) connecting the first part (52) and the second part (54) of the deadbolt (50) and extending between at least one first leaf (30) and at least one second leaf (32) when the door (28) is in the closed configuration, the hinge mechanism (62) comprising a hinge (64) allowing the first part (52) to move relative to the second part (54) along an axis of rotation (R3) substantially parallel to the vertical axis (Z-Z');in which, when the door (28) is in the closed configuration, when the deadbolt (50) is in the locked position, and in the event of depressurization, the door (28) is moved into the emergency configuration by the rotation of the first part (52) of the deadbolt; (50) relative to the second part (54) of the deadbolt (50) around the axis of rotation (R3) of the joint (64).

3. Portion of aircraft (10) according to claim 2, wherein the joint (64) is a pin joint comprising a pin (66) extending substantially parallel to the vertical axis (Z-Z').

4. Portion of aircraft (10) according to claim 2 or 3, wherein the hinge mechanism (62) further comprises a mechanical fuse (68) designed to: - prevent the rotation of the first part (52) of the deadbolt (50) relative to the second part (54) of the deadbolt (50) via the hinge (64) under normal flight conditions; - break in the event of depressurization, the breakage of the mechanical fuse (68) allowing the rotation of the first part (52) of the deadbolt (50) relative to the second part (54) of the deadbolt (50) via the hinge (64).

5. Portion of aircraft (10) according to claim 4, wherein, in the event of depressurization, the mechanical fuse (68) is designed to break under a pressure force greater than or equal to a force threshold, wherein the force threshold is less than or equal to the force generated by the depressurization on the door (28), and wherein the mechanical fuse (68) is designed to remain intact under forces less than the force threshold.

6. Portion of aircraft (10) according to claim 5, wherein the force threshold is between 550 N and 750 N.

7. Portion of aircraft (10) according to claim 5 or 6, wherein the mechanical fuse (68) is a fusible pin (70) extending substantially parallel to the axis of rotation (R3) of the joint (64), and wherein, in the event of depressurization, the fusible pin (70) breaks under the effect of a shear stress.

8. Portion of aircraft (10) according to claim 7, wherein a shear stress threshold corresponding to the force threshold is between 250 MPa and 500 MPa.

9. Portion of aircraft (10) according to claim 7, wherein the fusible pin (70) and the joint (64) are separated in a plane (PI) substantially perpendicular to the axis of rotation (R3) of the joint (64), by a distance (D2) between 10 mm and 15 mm.

10. Portion of aircraft (10) according to claim 7 or 8, wherein the fusible pin (70) is formed by an aluminum alloy, and wherein the fusible pin (70) has a diameter between 0.125 inch and 0.5 inch.

11. Portion of aircraft (10) according to any one of claims 2 to 10, wherein the hinge mechanism (62) further comprises a stop (74) and a complementary stop (76) designed to cooperate in order to limit the rotation of the first part (52) of the deadbolt (50) relative to the second part (54) of the deadbolt (50) via the hinge (64) to a maximum rotation in which the door (28) is in emergency configuration.

12. Portion of aircraft (10) according to any one of claims 2 to 11, wherein the strike plate (42) includes a housing (44) for receiving the first part (52) of the deadbolt (50) in the locked position, the deadbolt (50) including at least one bearing (56) designed to cooperate with inner walls (45) of the housing (44) during the movement of the deadbolt (50) between the locked and unlocked positions to guide the movement of the deadbolt (50).

13. Portion of aircraft (10) according to claim 12, wherein at least one bearing (56) is a ball bearing.

14. Portion of aircraft (10) according to claim 12 or 13, wherein the deadbolt (50) comprises at least two bearings (56) arranged side by side along the locking axis (B-B').

15. Portion of aircraft (10) according to any one of the preceding claims, wherein: - the minimum width (WMIN) of the aisle (36) near the door (28) is between 4 inches and 8 inches; - the optimal width (WOPT) of the aisle (36) near the door (28) is between 15 inches and 25 inches.

16. Portion of aircraft (10) according to any one of the preceding claims, wherein: - in the open configuration of the door (28), each of the at least one first leaf (30) and the at least one second leaf (32) forms an angle (Al) between 75° and 100° with the aisle axis (A-A'); - in the emergency configuration of the door (28), each of at least one first leaf (30) and at least one second leaf (32) forms an angle (A2) between 5° and 15° with the aisle axis (A-A').

17. Portion of aircraft (10) according to any one of the preceding claims, wherein the aircraft cabin (14) extends along a longitudinal axis (X-X') of the aircraft (1), the equipment (20) being arranged in a lateral portion (15) of the aircraft cabin (14), the aisle axis (A-A') being substantially parallel to the longitudinal axis (X-X') of the aircraft.

18. Portion of aircraft (10) according to any one of the preceding claims, wherein the equipment (20) is an aircraft lavatory.

19. Portion of aircraft (10) according to any one of the preceding claims, wherein the equipment (20) delimits the aisle (36) with a partition wall (17) from the portion of aircraft (10), the partition wall (17) extending substantially perpendicularly to the aisle axis (A-A') in a perpendicular plane (P3), the partition wall (17) from the portion of aircraft (10) comprising an edge (18) delimiting the aisle (36) with the equipment (20), wherein the first axis of rotation (RI) or the second axis of rotation (R2) of the gates (30, 32) extends in the perpendicular plane (P3), wherein the aisle (36) has a passage span (PS) corresponding to the minimum distance between: - the edge (18) of the partition wall (17); and - at least one first gate (30) or at least a second leaf (32); the passage span (PS) being: - between 4 inches and 8 inches in the open configuration of the door (28);- between 18 inches and 22 inches in the emergency door configuration (28).;

20. Aircraft (1) comprising a portion of an aircraft (10) according to any one of the preceding claims.

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