Airplane door with retractable means of holding the deployable evacuation device

Description

DOMAINE TECHNIQUE

[0001] The invention relates to the field of aeronautics and more particularly to aircraft doors equipped with a deployable evacuation device.

[0002] Aircraft whose access doors are located at a significant height above the ground when the aircraft is on the ground, including almost all airliners, are generally equipped with a deployable evacuation device such as a self-inflating slide mounted on the door opening.

[0003] These aircraft doors generally include means for retaining the deployable evacuation device, these means being adapted to occupy two positions: an armed position in which the means for retaining are fixed to the frame, to allow the triggering and fixing of the deployable evacuation device, in the event of evacuation; and an unarmed position in which the means for retaining are freely mobile relative to the frame to allow the door to be opened under normal operating conditions.

[0004] The restraint systems associated with the deployable evacuation device thus fulfill two functions: a first function in which they exert a pull on the trigger of the deployable evacuation device when the door is opened, which commands the deployment of the evacuation device; a second function in which they make the evacuation device fixed to the door frame once deployed, to allow evacuation. ART ANTÉRIEUR

[0005] Prior art aircraft doors incorporating a deployable evacuation device, as described in French patent application FR 2 576 217 A1, are generally equipped with a retaining bar connected by a curtain to the deployable evacuation device. Pulling on this retaining bar relative to the deployable evacuation device triggers its deployment. This retaining bar is adapted to cooperate with threshold jaws fixed to the door frame at the aircraft floor level. The door is locked by a downward movement of the door leaf relative to its frame, which engages stops located between the door leaf and the frame, and also positions the retaining bar in the jaws at the door threshold.

[0006] These threshold jaws are also equipped with a locking mechanism that allows the jaws to close onto the retaining bar. In the armed position, the jaws are locked onto the retaining bar, and if the door is opened for evacuation, the retaining bar remains engaged in the jaws. The opening movement of the door triggers the deployment of the evacuation device, which then remains attached to the door frame by the retaining bar, still locked in the jaws. In the disarmed position, the jaws are not locked, and the retaining bar is free to move relative to the jaws, at least in a lifting motion. In this disarmed position, when the door is unlocked by lifting it (to release the stops between the door and its frame), the retaining bar is released from the jaws, and the door can then be opened normally.

[0007] These earlier-style aircraft doors have a number of disadvantages.

[0008] First, for the deployable evacuation device to function, these doors require that they be locked and unlocked by a downward or upward movement of the door leaf relative to its frame. These devices therefore require a vertical movement of the door and cannot be used with doors that operate with a reciprocating motion, for example, doors that do not have any movement in the vertical direction.

[0009] These doors also require a complex mechanical device to actuate the locking of the threshold jaws from a control lever mounted on the door leaf.

[0010] Furthermore, threshold jaws are prominent elements that protrude from the aircraft floor. Their positioning options are limited to locations outside the standardized "clear opening" defined by regulations for passenger circulation. The protruding nature of the jaws also presents risks related to the accumulation of dust and objects (coins, etc.) that passengers may drop into the jaws, potentially disrupting their operation.

[0011] Furthermore, the structure of an aircraft in flight generally undergoes movements that result in relative displacements between the door and its sill. The connection between the retaining bar and the sill jaws must therefore be designed with ample clearance to accommodate this relative movement, leading to oversized sill jaws and a risk of unwanted mechanical noise due to vibrations.

[0012] There are also aircraft doors where the disengagement of the stops and opening movement is achieved through a sequence of rotations around two vertical axes. Such doors are characterized by the absence of vertical movement and exhibit significant retraction into the aircraft upon opening. The retention bar is engaged either manually or by means of a sliding mechanism. An intermediate piece supporting the retention bar is either slid onto the frame (armed) or onto the door leaf (disarmed). In both cases, the deployment of the evacuation device is triggered by pulling on the retention bar when the door opens. Manual engagement of the retention bar is no longer acceptable for new aircraft, and the mechanism associated with this type of door is complex and highly susceptible to jamming. EXPOSÉ DE L'INVENTION

[0013] The invention aims to improve prior art aircraft doors.

[0014] For this purpose, the invention relates to an aircraft door according to claim 1.

[0015] Another object of the invention relates to a method for opening such an aircraft door according to claim 12.

[0016] Such an aircraft door requires no protruding elements on the aircraft door sill, thus eliminating any safety issues, blockages, or susceptibility to dust or other nuisances at the sill. The second retaining device can therefore be positioned in the most optimal location, possibly within the standardized passage area.

[0017] The means for triggering the deployable evacuation device are completely independent of the aircraft door locking mechanisms. Such an aircraft door can therefore be locked or unlocked by any means, such as conventional up / down movements, but also, for example, by lateral escape movements of the door relative to the frame, or by controlled movable stop devices. The aircraft door equipped with the retention means according to the invention can thus be operated with all types of locking / unlocking mechanisms.

[0018] Furthermore, the restraint devices, although armed, only engage when the door is actually opened and sufficiently wide for the first restraint to engage with the second. In other words, the deployable evacuation device is only activated when the door has opened sufficiently, that is, when the user has indicated their intention to open the door by activating the deployable evacuation devices. A door opening that falls short of the point at which the first and second restraints engage allows the door to be reversed, returning it to the closed position without activating the deployable evacuation device.The aircraft door thus guarantees, even when armed, an initial door opening range (conditioned by the beam length) allowing the door to be opened by mistake, without consequences.

[0019] The invention departs from the common practice in the aeronautical field of arming restraint systems by engaging them in jaws while the aircraft is in flight, and disarming them only when the aircraft is on the ground. According to the invention, the restraint systems, when armed, can be in two positions: an armed position awaiting engagement; or an armed and engaged position. Thus, during flight, the restraint systems are armed but awaiting engagement, while the retraction mechanisms are in the primed position, so that if the door is opened, the restraint systems automatically move to the engaged position beyond a certain door opening range.

[0020] The invention thus makes it possible to make the restraint means independent of the relative movements between the door and the floor during the flight of the aircraft.

[0021] The aircraft door according to the invention may include the following additional features, alone or in combination: The opening comprises a door structure, and the beam is fixed to the door structure; the detachable clip has an elastically deformable fixing element for the first elastic element on the beam; the detachable clip has a fixing housing on the beam as well as an elastic tab, and the first retaining element has a fixing head adapted to be housed in the fixing housing and held in place by the elastic tab; the second retaining element is mounted on a portion of the threshold of the door frame; one of the first and second retaining elements has a retaining bar and the other of the first and second retaining elements has a hook that can be coupled to the retaining bar; the hook has a ratchet for retaining the retaining bar in the hook;The second retaining device is movable between a protruding position and a retracted position, the retraction means being associated with the second retaining device such that the engaged position of the retraction means causes the second retaining device to protrude, and the disengaged position of the retraction means causes the second retaining device to retract; the retraction means comprise a frame and a pivot axis on which the second retaining device is mounted to pivot between its retracted and protruding positions; the retraction means comprise an elastic means for pushing the second retaining device back into its stable protruding or retracted position; the door comprises two retaining assemblies arranged on either side of the opening. PRÉSENTATION DES FIGURES

[0022] Other features and advantages of the invention will become apparent from the following non-limiting description, with reference to the accompanying drawings in which: [ Fig.1 ] There figure 1 is a partial representation of a door according to the invention; [ Fig.2 ] There figure 2 is a perspective view of a set of retaining devices for the gate of the figure 1 , in a first position, the retraction mechanisms being in the primed position; [ Fig.3 ] There figure 3 is a profile view of the figure 2 ; Fig.4 ] There figure 4 is a perspective view of the restraint assembly in a second position, with the retraction means in the primed position; [ Fig.5 ] There figure 5 is a profile view of the figure 4 ; Fig.6 ] There figure 6 is a perspective view of the entire restraint assembly in a third position, with the retraction means in the primed position; [ Fig.7 ] There figure 7 is a profile view of the figure 6 ; Fig.8 ] There figure 8 is a perspective view of the restraint assembly in a fourth position, with the retraction means in the primed position; [ Fig.9 ] There figure 9 is a profile view of the figure 8 ; Fig.10 ] There figure 10 is a perspective view of the entire restraint system in a first position, with the retraction means in the disarmed position; [ Fig.11 ] There figure 11 is a profile view of the figure 10 ; Fig.12 ] There figure 12 is a perspective view of the restraint assembly in a second position, with the retraction means in the disarmed position; [ Fig.13 ] There figure 13 is a profile view of the figure 12 ; Fig.14 ] There figure 14 is a perspective view of the entire restraint assembly in a third position, with the retraction means in the disarmed position; [ Fig.15 ] There figure 15 is a profile view of the figure 14 . DESCRIPTION DÉTAILLÉE

[0023] There figure 1 represents in perspective a portion of an aircraft door according to the invention. This illustrative view represents the bottom of the aircraft door in place in the fuselage 1 of an aircraft.

[0024] The aircraft door comprises an opening 2 and a frame 3. On the figure 1 The door is shown in the closed position. The door is also adapted to occupy an open position in which the leaf 2 is free from the frame 3. For this purpose, the door includes a locking / unlocking and opening / closing mechanism, which is not the subject of the invention and will therefore not be described in further detail here. These known mechanisms allow the leaf 2 to move between the closed position shown in the figure 1 and an opening position where the opening 2 is moved against the outside of the fuselage leaving the passage open through the frame 3.

[0025] The frame 3 consists of a structure arranged around the opening 2 and fixed to the fuselage 1 of the aircraft. This frame 3 also includes a portion of a sill 4 extending under the floor 5 of the aircraft.

[0026] The aircraft door includes a deployable evacuation device 6, such as a self-inflating slide, mounted on the opening 2 (shown schematically in dotted lines on the figure 1 ).

[0027] The aircraft door also includes restraint means connected to the deployable evacuation device 6 to enable its activation and attachment to the door frame 3. These restraint means comprise two identical sets of restraints 7.

[0028] There figure 2 is an enlarged view of a portion of the figure 1 and represents one of the 7 retention sets in more detail. The figure 3 is a profile view of the entire retaining assembly 7 shown in the figure 2 Each of the 7 carry sets comprises: a beam 8, one end of which 9 is fixed on the opening 2; a first retaining device 10 fixed on a second end 11 of the beam 8; a second retaining device 12 fixed, in this example, on the portion of the threshold 4 of the frame 3.

[0029] On the figure 3 , the aircraft floor 5 has not been shown, which makes visible the chassis 22 supporting the second restraint device 12.

[0030] In this example, the first retaining element 10 consists of a bracket 13 supporting a retaining bar 14 that extends substantially orthogonally to the direction in which the beam 8 extends. The first retaining element 10 also includes a fastening head 15 that is inserted into a fastening housing 16 attached to the second end 11 of the beam 8. The fastening head 15 is held inside the fastening housing 16 by an elastic retaining means, which in this case consists of an elastic tab 17. The fastening housing 16 and the elastic tab 17 thus form a detachable clip for attaching the first retaining element 10 to the beam 8. This clip formed by the fastening housing 16 and the elastic tab 17 is said to be detachable because if sufficient tensile force is applied to the retaining bar 14, the first retaining element 10 detaches from the beam 8.In this example, the detachable clip is fixed to the beam 8 and receives the first retaining element 10, allowing its detachment. Alternatively, the detachable clip can be fixed to the first retaining element 10 and allow the latter to detach from the beam 8.

[0031] The first restraint device 10 is further connected to the deployable evacuation device 6 by straps 19 (see figure 1 ).

[0032] Beam 8 is fixed to the opening 2 so that beam 8 extends substantially perpendicularly to the opening 2. In this example, the opening 2 includes a set of reinforcing beams 18 (see figure 1 ) and beam 8 is fixed on one of these beams 18. Beam 8 is said to be substantially perpendicular to the opening 2 insofar as this beam 8 extends transversely to the opening 2, at angles close to 80° to 100°.

[0033] The second retaining element 12 includes a hook 20 and a ratchet 21. The second retaining element 12 is complementary to the first retaining element 10, because the retaining bar 14 is adapted to fit into the hook 20.

[0034] The restraint assemblies 7 also each include means for retracting the second restraint 12, movable between a primed position in which the second restraint 12 protrudes from the floor 5 of the aircraft (position visible to figures 1 à 3 ), and a disarmed position in which the second restraint 12 is retracted into the aircraft floor 5 (see figure 10 ).

[0035] In the position of the figure 1 The restraints of the deployable evacuation device 6 are in the disarmed position, as the first restraint 10 is freely movable relative to the second restraint 12. However, the retraction means are in the primed position. This configuration corresponds, for example, to the aircraft's flight configuration, in which deployment of the deployable evacuation device 6 is required if the door is opened.

[0036] Based on this configuration of figures 1 à 3 The door opening sequences that will trigger the deployable evacuation device 6 will now be described with reference to figures 4 à 9 .

[0037] The initial positioning of the retracting means leads to the positioning of the hook 20 on the path of the retaining bar 14 when the door is opened. In this example, opening the door causes the door leaf 2 to move outwards from the fuselage 1.

[0038] During this movement, the trajectory of the opening 2 causes a displacement of the first retaining member 10 relative to the second retaining member 12 until the retaining bar 14 meets the ratchet 21 (position shown in figures 4 And 5 ). THE figures 4 And 5 represent, respectively in perspective and in profile, this position where the retaining bar 14 comes to push back the ratchet 21.

[0039] There figure 5 represents the second retaining element 12 without its frame 22, thus revealing the internal components of the second retaining element 12. The second retaining element 12 includes a pivot axis 23 by which the hook 20 is rotatably mounted on the frame 22. The pawl 21 is rotatably mounted on the hook 20 and closes the opening of the hook 20 by means of a return spring 24. A gas spring 25 acts as a spring and maintains the hook 20 in its two stable positions (protruding as on the figure 5 or retracted).

[0040] Between the positions of figures 1 à 3 and that of the figures 4 And 5The aircraft door has a range of opening movement for the door leaf 2 within which the restraints remain in a state of readiness for engagement, even though they are already armed. Within this range, the door leaf 2 can therefore be closed (for example, if it has been opened accidentally) without the restraints, although armed, having moved into the engaged position, and thus without risk of triggering the deployable evacuation device 6.

[0041] THE figures 6 And 7 These figures represent, respectively in perspective and profile, the position in which the retaining bar 14 is engaged in the hook 20, a position that occurs when the opening movement continues. The ratchet 21 has returned to its position and prevents the first retaining element 10 and the second retaining element 12 from disengaging. This position of the figures 6 And 7corresponds to an automatic switching of the restraint means into the engaged position.

[0042] Continuing to open the door then leads to the position illustrated in the figures 8 And 9 representing the entire retention system in perspective and profile views, respectively. From the position of the figures 6 And 7 The retaining bar 14 remains caught in the hook 20 and the continuation of the movement leads to a pull on the attachment 16, 17 causing a detachment of the first retaining member 10 and the beam 8. The tensile force between the beam 8 and the first retaining member 10 leads in fact to the elastic deformation of the elastic tongue 17 so that the fixing head 15 is extracted from the fixing housing 16.

[0043] The continuation of the opening movement, beyond the position of figures 8 And 9This then leads to the opening of the door while the first retaining device 10 remains attached to the second retaining device 12, and therefore to the frame 3. The first retaining device 10 is connected to the deployable evacuation device 6 by the strap 19 (not shown in the figures 2 à 15 ), the movement of the opening which incorporates the deployable evacuation device causes a pull of the strap 19 on the trigger, and therefore causes the deployable evacuation device to be triggered.

[0044] The link between the deployable evacuation device 6 and the frame 3 is therefore made by the first restraint device 10 which is kept attached to the second restraint device 12.

[0045] The means for retracting the second retaining element 12 include, in this example, the frame 22 and the pivot axis 23, the gas spring 25, and any control means (not shown) allowing the hook 20 to be tilted between its two positions: extended and retracted. These control means can be implemented by any mechanical and / or electrical means suitable for driving the pivoting of the hook 20, such as, for example, an electric motor, a rack and pinion, a lever and cam system, etc. These retracting means are actuated when the second retaining element 12 is to be configured in one of its positions. protruding, which causes the restraint means to automatically move into the engaged position when the door is opened and only when the door is opened, the restraint means being in the armed position but waiting to be engaged until the door has been manipulated; retracted, which allows free opening of the door, keeping the restraint means in the disarmed position, and therefore without triggering the deployable evacuation device 6.

[0046] The door opening configuration in normal operation, in which the retracting means are in the disengaged position, will now be described with reference to figures 10 à 15 This disengaged position of the retracting means corresponds to a normal aircraft door opening situation on the ground, i.e., when airport equipment for passenger boarding and disembarking is in place. The crew then activates the retracting means in their disengaged position, which, in this example, results in the second retaining device 12 remaining in its retracted position.

[0047] There figure 10 And 11 are views similar respectively to figures 2 And 3 except that the retraction mechanisms are in their disarmed position. In this configuration, the restraint mechanisms remain in the disarmed position and will not automatically switch to the engaged position when the door is opened.

[0048] Based on the positions of the figures 10 And 11, an opening movement of the opening 2 causes a displacement of the beam 8 to the position of the figures 12 And 13 . In this configuration, the second restraint 12, which is in the retracted position, is no longer on the path of the first restraint 10 and the restraint bar 14 passes opposite the second restraint 12 without interacting with the latter.

[0049] The door opening movement then continues until the position of figures 14 And 15 in which the opening 2 opens without the deployable evacuation device 6 being triggered.

[0050] Alternative embodiments of the aircraft door can be implemented without departing from the scope of the invention. In particular, the detachable clip can be made by any other means, for example by an assembly with a breakable pin, allowing the first retaining element 10 to be fixed to the beam 8, and being detachable when a tensile force exceeding a predetermined threshold is applied to the retaining element 10.

[0051] Similarly, the coupling means between the first and second retaining devices can be made differently; the first retaining device can be fitted with a hook and the second retaining device can be fitted with a retaining bar, for example, or any other configuration of coupling means.

[0052] Furthermore, the example described above involves a second restraint 12 that retracts into the aircraft floor. However, it is also possible to provide for the retraction means to act on the first restraint 10, for example, by folding it against the beam, so that the activated position causes the first restraint to deploy, and the deactivated position causes it to retract. The second restraint is thus either present or absent in the path of the first restraint when the door is opened. In such an example, the second restraint and its hook are therefore fixed. This fixed hook protrudes more than the retractable hook described in the example, however, its overall size remains significantly reduced compared to the prominent jaws of the prior art.

Claims

1. An aircraft door comprising: - a door frame (3), having a threshold portion to extend under a floor (5); - a leaf (2) having an internal face intended to be turned toward the interior of the aircraft, the leaf (2) being movable with respect to the door frame (3) between a closed position and an open position; - a deployable evacuation device (6) mounted on the leaf (2); - retaining means comprising at least one retaining assembly (7) comprising a first retaining member (10) connected to the deployable evacuation device (6) and a second retaining member (12), couplable to the first retaining member (10), mounted on the door frame (3), said retaining means being designed to assume: an armed and engaged position, in which the first retaining member (10) of the retaining means is secured to the second retaining member mounted on the door frame (3), and a disarmed position, in which the first retaining member (10) of the retaining means is freely movable relative to the second retaining member (12) mounted on the door frame (3); this aircraft door being characterized in that each retaining assembly (7) comprises: - a beam (8) having a first end (9) fixed to the internal face of the leaf (2) and a second end (11) on which the first retaining member (10) is fixed in a detachable manner by a clip (16, 17), this beam (8) extending substantially perpendicularly to the leaf (2); - retraction means (22, 23, 25) for retracting the second retaining member (12) that are movable between: a primed position, in which the second retaining member (12) protrudes from the floor (5) in the path of the first retaining member (10) when the leaf (2) passes from its closed position to its open position; and a deactivated position, in which the second retaining member (12) is retracted into the floor outside the path of the first retaining member (10) when the leaf (2) passes from its closed position to its open position.

2. The aircraft door as claimed in claim 1, characterized in that the leaf (2) comprises a door structure (18), and in that the beam (8) is fixed to the door structure (18).

3. The aircraft door as claimed in either one of the preceding claims, characterized in that the detachable clip has an elastically deformable fixing element (17) for fixing the first elastic member (10) to the beam (8).

4. The aircraft door as claimed in claim 3, characterized in that the detachable clip has a fixing receiving portion (16) on the beam (8) and also an elastic tab (17), and the first retaining member (10) has a fixing head (15) designed to be received in the fixing receiving portion (16) and to be held in place by the elastic tab (17).

5. The aircraft door as claimed in any one of the preceding claims, characterized in that the second retaining member (12) is mounted on a threshold portion (4) of the door frame (3).

6. The aircraft door as claimed in any one of the preceding claims, characterized in that one of the first (10) and the second (12) retaining member has a retaining bar (14) and the other of the first (10) and the second (12) retaining member has a hook (20) couplable to the retaining bar (14).

7. The aircraft door as claimed in claim 6, characterized in that the hook (20) has a pawl (21)for holding the retaining bar (14) in the hook (20).

8. The aircraft door as claimed in any one of the preceding claims, characterized in that the second retaining member (12) is movable between a protruding position and a retracted position, the retraction means being associated with the second retaining member (12) such that the primed position of the retraction means triggers the protruding position of the second retaining member (12), and the deactivated position of the retraction means triggers the retracted position of the second retaining member (12).

9. The aircraft door as claimed in claim 8, characterized in that the retraction means have a chassis (22) and a pivot pin (23) on which the second retaining member (12) is mounted pivotably between its retracted position and its protruding position.

10. The aircraft door as claimed in claim 9, characterized in that the retraction means have an elastic means (25) pushing the second retaining member (12) back into its stable protruding or retracted position.

11. The aircraft door as claimed in any one of the preceding claims, characterized in that it has two retaining assemblies (7) arranged on either side of the leaf (2).

12. A method for opening the aircraft door as claimed in one of the preceding claims, characterized in that it has the following steps: - placing the retraction means in the primed position; - driving the leaf (2) in an opening movement along a first travel in which the first retaining member (10) is driven until it meets the second retaining member (12); - continuing the opening movement of the leaf (2) along a second travel in which the first retaining member (10) remains coupled to the second retaining member (12) and comes away from the beam (8).