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BR-102025014105-A2 - Portion of aircraft comprising a safety equipment door for depressurization and aircraft.

BR102025014105A2BR 102025014105 A2BR102025014105 A2BR 102025014105A2BR-102025014105-A2

Abstract

This refers to the portion of aircraft (10) comprising a piece of equipment (20) comprising: - an outer wall (22) delimiting a compartment (24); - a door (28) facing a corridor (36) and movable between a closed and an open configuration; wherein the corridor (36) has: - a maximum width when the door (28) is in the closed configuration; - a minimum width when the door (28) is in the open configuration; and wherein, when the door (28) is in the closed configuration and in case of depressurization, the door (28) is moved and maintained in an emergency configuration wherein the corridor (36) has an ideal width that corresponds to a width sufficient to simultaneously: - allow air to escape from the compartment (24); and - allow passengers to walk through the corridor (36) beyond the piece of equipment (20).

Inventors

  • Gregory Lefloch

Assignees

  • DASSAULT AVIATION

Dates

Publication Date
20260310
Application Date
20250708
Priority Date
20240711

Claims (20)

  1. 1. AIRCRAFT PORTION (10) characterized by comprising: - a fuselage (12) that delimits the cabin of an aircraft (14); - a piece of equipment (20) that delimits, with another piece of equipment (88) or with a wall (16) of the aircraft portion (10), a corridor (36) that extends along a geometric axis of the corridor (A-A’), wherein the corridor (36) has a width measured according to a transverse geometric axis (Y-Y') substantially perpendicular to the geometric axis of the corridor (A-A’), wherein the piece of equipment (20) comprises: - an outer wall (22) that delimits a compartment (24); - a door (28) facing the corridor (36) and comprising at least one first leaf (30) and at least one second leaf (32), wherein each of the at least one first leaf (30) and the at least one second leaf (32) is rotatably mounted on the outer wall (22), respectively, along a first geometric axis of rotation (R1) and a second geometric axis of rotation (R2), wherein the door (28) is able to move between: - a closed configuration in which at least one first leaf (30) and at least one second leaf (32) prevent access to the compartment (24), extending both in a plane substantially parallel to the geometric axis of the corridor (A-A’) and in a vertical geometric axis (Z-Z') substantially perpendicular to the geometric axis of the corridor (A-A’) and to the transverse geometric 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 corridor (36) to give access to the compartment (24); wherein, near the door (28), the corridor (36) has: - a maximum width when the door (28) is in the closed configuration; - a minimum width when the door (28) is in the open configuration; wherein, when the door (28) is in the closed configuration and in case of depressurization, the door (28) is moved and maintained in an emergency configuration that is between the closed configuration and the open configuration, wherein, next to the door (28), the corridor (36) has an ideal width that is between the maximum width and the minimum width and that corresponds to a width sufficient to simultaneously: - allow air to escape from the compartment (24); and - allow passengers to walk through the corridor (36) beyond the piece of equipment (20).
  2. 2. AIRCRAFT PORTION (10), according to claim 1, characterized by further comprising a locking system (40) comprising a door locking mechanism (42) mounted on at least one first leaf (30) and a lock (50) mounted on at least one second leaf (32), wherein the lock (50) is movable in translation along a geometric locking axis (B-B’), which is substantially parallel to the geometric axis of the corridor (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 lock (50) cooperates with the door locking mechanism (42) to maintain the door (28) in the closed configuration; - an unlocking position in which, when the door (28) is in the closed configuration, the lock (50) is moved away from the door locking mechanism (42) to allow the door (28) to move to from the closed configuration to the open configuration; the lock (50) comprising: - a first portion (52) designed to extend within the door locking mechanism (42) in the locking position; - a second portion (54) mounted on at least one second leaf (32); and a hinge mechanism (62) connecting the first portion (52) and the second portion (54) of the lock (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, wherein the hinge mechanism (62) comprises a joint (64) that allows movement of the first portion (52) relative to the second portion (54) along a geometric axis of rotation substantially parallel to the vertical geometric axis (Z-Z'); wherein, when the door (28) is in the closed configuration, when the lock (50) is in the locking position and in case of depressurization, the door (28) is moved to the emergency configuration by rotation of the first portion (52) of the lock (50) relative to the second portion (54) of the lock (50) around the geometric axis of rotation (R3) of the joint (64).
  3. 3. AIRCRAFT PORTION (10), according to claim 2, characterized in that the joint (64) is a joint (64) of pins (66) comprising a pin (66) extending substantially parallel to the vertical geometric axis (Z-Z').
  4. 4. AIRCRAFT PORTION (10), according to any one of claims 2 to 3, characterized in that the articulation mechanism (62) further comprises a mechanical fuse (68) designed to: - prevent rotation of the first portion (52) of the lock (50) relative to the second portion (54) of the lock (50) through the joint (64) under normal flight conditions; - break in case of depressurization, wherein the break of the mechanical fuse (68) allows rotation of the first portion (52) of the lock (50) relative to the second portion (54) of the lock (50) through the joint (64).
  5. 5. AIRCRAFT PORTION (10), according to claim 4, characterized in that, in case of depressurization, the mechanical fuse (68) is designed to break under a pressure load greater than or equal to a load threshold, wherein the load threshold is less than or equal to the load generated by depressurization at the door (28), and wherein the mechanical fuse (68) is designed to remain intact under loads less than the load threshold.
  6. 6. AIRCRAFT PORTION (10), according to claim 5, characterized by the load threshold being between 550 N and 750 N.
  7. 7. AIRCRAFT PORTION (10), according to any one of claims 5 to 6, characterized in that the mechanical fuse (68) is a fuse pin (70) that extends substantially parallel to the geometric axis of rotation (R3) of the joint (64) and in that, in case of depressurization, the fuse pin (70) breaks under shear stress.
  8. 8. AIRCRAFT PORTION (10), according to claim 7, characterized by a shear stress limit corresponding to the load threshold being between 250 MPa and 500 MPa.
  9. 9. AIRCRAFT PORTION (10), according to any one of claims 7 to 8, characterized in that the fuse pin (70) and the joint (64) are separated in a plane substantially perpendicular to the geometric axis of rotation (R3) of the joint (64), by a distance between 10 mm and 15 mm.
  10. 10. AIRCRAFT PORTION (10), according to any one of claims 7 to 9, characterized in that the fuse pin (70) is made of an aluminum alloy and in that the fuse pin (70) has a diameter between 0.32 cm and 1.27 cm (0.125 inches and 0.5 inches).
  11. 11. AIRCRAFT PORTION (10), according to any one of claims 2 to 10, characterized in that the articulation mechanism (62) further comprises a stop (74) and a supplementary stop (76) designed to cooperate to limit the rotation of the first portion (52) of the lock (50) relative to the second portion (54) of the lock (50) via the joint (64) to a maximum rotation in which the door (28) is in the emergency configuration.
  12. 12. AIRCRAFT PORTION (10), according to any one of claims 2 to 11, characterized in that the door locking mechanism (42) comprises a housing (44) designed to receive the first portion (52) of the lock (50) in the locking position, wherein the lock (50) comprises at least one bearing (56) designed to cooperate with the inner walls (45) of the housing (44) during the movement of the lock (50) between the locking and unlocking positions to guide the movement of the lock (50).
  13. 13. AIRCRAFT PORTION (10), according to claim 12, characterized in that at least one bearing (56) is a ball bearing.
  14. 14. AIRCRAFT PORTION (10), according to any one of claims 12 to 13, characterized in that the lock (50) comprises at least two bearings (56) arranged side by side along the geometric axis of the lock (B-B’).
  15. 15. AIRCRAFT PORTION (10), according to any one of claims 1 to 14, characterized by: - the minimum width of the aisle (36) near the door (28) being between 10.16 and 20.32 cm (4 and 8 inches); - the ideal width of the aisle (36) near the door (28) being between 38.1 and 63.5 cm (15 and 25 inches).
  16. 16. AIRCRAFT PORTION (10), according to any one of claims 1 to 15, characterized by: - in the open configuration of the door (28), each of at least one first leaf (30) and at least one second leaf (32) forming an angle between 75° and 100° with the geometric axis of the corridor (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) forming an angle between 5° and 15° with the geometric axis of the corridor (A-A’).
  17. 17. AIRCRAFT PORTION (10), according to any one of claims 1 to 16, characterized in that the aircraft cabin (14) extends along a longitudinal geometric axis (X-X') of the aircraft (1), the piece of equipment (20) being disposed in a side part (15) of the aircraft cabin (14), the geometric axis of the corridor (A-A’) being substantially parallel to the longitudinal geometric axis (X-X') of the aircraft (1).
  18. 18. AIRCRAFT PORTION (10), according to any one of claims 1 to 17, characterized in that the piece of equipment (20) is an aircraft toilet.
  19. 19. AIRCRAFT PORTION (10), according to any one of claims 1 to 18, characterized in that the piece of equipment (20) delimits the corridor (36) with a partition wall (17) of the aircraft portion (10), wherein the partition wall (17) extends substantially perpendicular to the geometric axis of the corridor (A-A’) in a perpendicular plane (P3), wherein the partition wall (17) of the aircraft portion (10) comprises an edge (18) that delimits the corridor (36) with the piece of equipment (20), wherein the first geometric axis of rotation (R1) or the second geometric axis of rotation (R2) of the sheets (30, 32) extends to the perpendicular plane (P3), wherein the corridor (36) has a passage gap (PS) which is the minimum distance between: - the edge (18) of the partition wall (17); and at least one first leaf (30) or at least one second leaf (32); the passage opening (PS) being: - between 10.16 cm and 20.32 cm (4 inches and 8 inches) in the open configuration of the door (28); - between 45.72 cm and 55.88 cm (18 inches and 22 inches) in the emergency configuration of the door (28).
  20. 20. AIRCRAFT (1) characterized by comprising an aircraft portion (10), as defined in any one of claims 1 to 19.

Description

[001] The present invention relates to a portion of an aircraft comprising: - a fuselage that delimits the cabin of an aircraft; - a piece of equipment that delimits, with another piece of equipment or with a wall of the portion of the aircraft, a corridor that extends along a geometric axis of the corridor, the corridor having a width measured according to a transverse geometric axis substantially perpendicular to the geometric axis of the corridor, the piece of equipment comprising: - an outer wall that delimits a compartment; - a door facing the corridor comprising at least one first leaf and at least one second leaf, each of the at least one first leaf and at least one second leaf being rotatably mounted on the outer wall, respectively, along a first geometric axis of rotation and a second geometric axis of rotation, the door being capable of moving between: - a closed configuration in which at least one first leaf and at least one second leaf prevent access to the compartment, extending either in a plane substantially parallel to the geometric axis of the corridor or in a vertical geometric axis substantially perpendicular to the geometric axis of the corridor. from the corridor and to the transverse geometric axis; - an open configuration in which at least one first leaf and at least one second leaf extend at least partially into the corridor to provide access to the compartment; in which, near the door, the corridor has: - a maximum width when the door is in the closed configuration; - a minimum width when the door is in the open configuration. [002] In such a portion of the aircraft, in the event of depressurization (i.e., loss of cabin pressurization), the air trapped inside the equipment compartment (e.g., a toilet) must be evacuated, especially when the compartment is responsible for a significant volume of air. Evacuating the air from inside the compartment prevents the outer wall from rupturing and parts of the outer wall and/or door from breaking. [003] When the door is in the closed position, and in particular when the door is locked in the closed position, the air contained within the compartment cannot escape. If the pressure difference is high enough, this can lead to the lock breaking and the door shifting to the open position. This is unsatisfactory because in the open position the door extends into the aisle and obstructs the aisle. This can interfere with the passenger's exit through the aisle. [004] There is therefore a need for a door system that increases passenger safety, particularly in the event of depressurization. [005] One of the objectives of the invention, therefore, is to provide an aircraft component that increases passenger safety, particularly in the event of depressurization. [006] To this end, the invention relates to a portion of an aircraft comprising: - a fuselage delimiting the cabin of an aircraft; - a piece of equipment that delimits, with another piece of equipment or with a wall of the portion of the aircraft, a corridor extending along a geometric axis of the corridor, the corridor having a width measured according to a transverse geometric axis substantially perpendicular to the geometric axis of the corridor, the piece of equipment comprising: - an outer wall delimiting a compartment; - a door facing the corridor comprising at least one first leaf and at least one second leaf, each of the at least one first leaf and at least one second leaf being rotatably mounted on the outer wall, respectively, along a first geometric axis of rotation and a second geometric axis of rotation, the door being capable of moving between: - a closed configuration in which at least one first leaf and at least one second leaf prevent access to the compartment, extending both in a plane substantially parallel to the geometric axis of the corridor and in a vertical geometric axis substantially perpendicular to the geometric axis of the corridor and to the transverse geometric axis; - an open configuration in which at least one first leaf and at least one second leaf extend at least partially into the corridor to give access to the compartment; in which, near the door, the corridor has: - a maximum width when the door is in the closed configuration; - a minimum width when the door is in the open configuration; and in which, when the door is in the closed configuration and in case of depressurization, the door is moved and maintained in an emergency configuration that is between the closed configuration and the open configuration, in which, near the door, the corridor has an ideal width that is between the maximum width and the minimum width and that corresponds to a width sufficient to simultaneously: - allow air to escape from the compartment; and - allow passengers to walk through the corridor beyond the piece of equipment. [007] Due to the invention, when the door is in the closed configuration and in case of depressurization, the door is opened enough to allow the air trapped ins