• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The subject of the invention is a cockpit for an airplane which comprises an escape opening closed by an emergency door (60) and an emergency hatch (72). The emergency hatch (72) comprises a fabric (84) and a locking / unlocking mechanism (88) configured to occupy a locked state in which the fabric (84) closes the discharge opening (58) and an unlocked state wherein the fabric (84) disengages the discharge opening (58).
    公开号:FR3032420A1
    申请号:FR1551100
    申请日:2015-02-11
    公开日:2016-08-12
    发明作者:Vincent Auriac；Loic Challancin
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a cockpit of an aircraft equipped with an emergency evacuation closed by an emergency door and an emergency hatch. As illustrated in FIGS. 1 and 2, an aircraft comprises a skin 10 forming the fuselage, an inner partition 14 which delimits a cockpit 12.
    [0002] The aircraft includes, for evacuating the pilots, an evacuation opening 18 making it possible to communicate the interior of the cabin 12 with the outside 20 of the aircraft and at least one emergency door 22 making it possible to close off or disengage the vehicle. Exhaust opening 18. According to an embodiment illustrated in Figure 1, this emergency door 22 is positioned on the upper part of the fuselage, directly above the cockpit 12. This emergency door 22 comprises a wall with an outer surface 24 in the continuity of the outer surface of the skin 10 of the fuselage. This emergency door 22 comprises a hinge 26 allowing it to pivot inwardly of the cabin and locking / unlocking means 28 controlled by an interior opening control 30 operable from inside the fuselage and by a control of external opening 32 operable from outside the fuselage. Inside the fuselage, the aircraft includes an emergency hatch 34 which closes the discharge opening 18 and ensures the continuity of the interior partition 14 of the cabin 12. This emergency hatch 34 is in the form of a rigid panel which comprises: on one side, goosenecks 36 configured to allow the emergency hatch 34 to pivot in the open position and to disengage from the inner partition 14, on a second side opposite to the first side, a locking / unlocking mechanism 38 configured to occupy a locked state in which the mechanism 38 keeps the emergency hatch 34 in the closed position and an unlocked state in which it no longer holds the emergency hatch 34 in the closed position and allows its pivoting through to the goosenecks 36, 3032420 2 on one side of the emergency hatch 34 facing the interior of the cabin, a first control 40 configured to cause the passage of the mech In the unlocked state when actuated by a person from inside the cabin, on one side of the emergency hatch 34 facing the emergency door 22, a second control 42 configured to cause the passage of the locking / unlocking mechanism 38 in the unlocked state when it is actuated by the emergency door 22 when it is opened. The first control 40 is a handle connected to the locking / unlocking mechanism 38. The second control 42 is a pivoting lever which is connected via a cable to the locking / unlocking mechanism 38. According to this configuration, the weight the emergency hatch 34 facilitates its pivoting towards the inside of the cabin when it is no longer held by the locking / unlocking mechanism 38. Therefore, the emergency hatch 34 must have a certain mass to function properly. . Also, the present invention aims to provide an emergency hatch which provides the same functions as a hatch of the prior art while having a lower mass. For this purpose, the subject of the invention is an aircraft control cabin comprising an outer skin attached to a structure, an inner partition delimiting the cabin, and a discharge opening passing through said outer skin and said inner partition, said discharge opening being closed by: an emergency door mounted articulated on the structure between a closed position in which the emergency door is arranged in the extension of the outer skin and closes said discharge opening and an open position in The emergency door pivots inwardly of the cabin, said emergency door comprising locking / unlocking means; an emergency hatch movable between a closed position in which the emergency hatch ensures the continuity of the partition; interior of the cabin and an open position, said emergency door comprising a locking / unlocking mechanism. According to the invention, the emergency hatch comprises a fabric permanently connected to the structure, by a first side and the locking / unlocking mechanism comprises: a first part integral with a second side, opposite to the first side and a second part secured to the structure, the first and second parts cooperating in the locked state so as to hook the second side of the fabric to the structure, a rod secured to the second side and a lever operable from the cab and connected to said rod. The fact of choosing an emergency hatch in the form of a fabric makes it possible to reduce the weight on board compared with a hatch of the prior art. Preferably, the fabric is elastic or comprises at least one elastic band so that the fabric is stretched when it closes the discharge opening. This configuration 10 facilitates the transition from the locked state to the unlocked state. Thus, it is not the weight of the emergency hatch which favors its opening but the elasticity of the fabric. According to a first variant, the first part of the locking / unlocking mechanism comprises a hook integral with the rod and which cooperates with the second part comprising a keeper.
    [0003] According to this first variant, the emergency hatch comprises at least one stabilization tab secured to the structure, configured to limit the tilting of the rod towards the emergency door when the fabric closes the discharge opening. According to this first variant, the locking / unlocking mechanism comprises a lever which comprises a first end connected to the rod and a second end facing the emergency door, said lever being automatically actuable by said emergency door when it is pivoted towards inside the cabin. According to a second variant, the locking / unlocking mechanism comprises a second rod which comprises at least one hook configured to retain the first rod, said second rod being connected to the structure via a pivoting connection so as to occupy a holding position in which the hook retains the first rod and a rotated position in which the hook no longer retains the first rod. According to this second variant, the locking / unlocking mechanism comprises at least one torsion spring configured to hold the second rod in the holding position.
    [0004] Preferably, according to this second variant, the locking / unlocking mechanism comprises a lever which has a first end connected to the second rod and a second end facing the emergency door, said lever being automatically actuable by said door. relief when pivoting into the cabin. Other features and advantages will become apparent from the following description of the invention, a description given by way of example only, with reference to the accompanying drawings in which: FIG. 1 is a perspective view of the front of an airplane illustrating an emergency door, positioned above a flight deck, FIG. 2 is a diagrammatic section of a discharge opening according to the prior art, FIG. 3 is a diagrammatic section of a FIG. 4 is a perspective view of a portion of an emergency hatch according to a first variant of the invention. FIGS. 5A to 5D are diagrams illustrating FIG. the principle of operation of the emergency hatch visible in FIG. 4 actuated from the inside, FIG. 6 is a perspective view illustrating the principle of operation of the emergency hatch visible in FIG. 4 actuated from the outside, The FIG. 7 is a perspective view of a portion of an emergency hatch according to a second variant of the invention. FIGS. 8A to 8C are diagrams illustrating the principle of operation of the emergency hatch shown in FIG. 7 9 is a perspective view illustrating the principle of operation of the emergency hatch visible in Figure 7 actuated from the outside. In FIG. 3, there is shown a part of an aircraft which comprises a fuselage with an outer skin 50 attached to a structure 52, and inside the fuselage, a cabin 54 delimited by an inner partition 56 spaced from the skin 50. The aircraft comprises at least one discharge opening 58 which allows the interior of the cabin 54 to communicate with the outside of the aircraft. According to an implementation, the discharge opening 58 is positioned on the upper part of the fuselage, in line with the cockpit. For the rest of the description, as shown in FIG. 1, a longitudinal direction DL corresponds to the direction that extends from the front tip to the rear tip of the aircraft. A transverse plane 3032420 is a plane perpendicular to the longitudinal direction. A radial direction DR is a direction perpendicular to the longitudinal direction. According to one configuration, the discharge opening 58 is delimited by a duct comprising a front wall comprised in a first transverse plane, a rear wall 5 included in a second transverse plane, a lower wall and an upper wall parallel to the longitudinal direction. and curved portions connecting the different walls. Thus, the discharge opening 58 has an approximately square or rectangular section with rounded corners. However, the discharge opening 58 is not limited to this geometry and other shapes are possible. The discharge opening 58 is closed by a removable emergency door 60 positioned in the extension of the skin 50 and whose geometry is adapted to that of the discharge opening 58. This emergency door 60 comprises a wall with an outer surface 62 in the continuity of the outer surface of the skin 50 of the fuselage when the emergency door 60 closes the discharge opening 58. The emergency door 60 comprises locking / unlocking means 64 controlled by a internal opening control 66 operable from the inside of the fuselage and by an external opening control 68 operable from outside the fuselage. According to one embodiment, the emergency door 60 is connected to the structure 52 of the aircraft 20 by a pivot axis 70 parallel to one of the walls of the discharge opening. It is preferably positioned at the rear wall of the discharge opening 58. When the locking / unlocking means 64 are in the unlocked state, the emergency door 60 can pivot about the pivot axis 70 towards the inside of the fuselage. The aircraft comprises at the level of the discharge opening 58 and the internal partition 56, an emergency door 72 movable between a closed position in which it closes the discharge opening 58 and an open position in which it This escape hatch 72 is arranged in the continuity of the inner partition 56 in the closed position. According to one embodiment, the emergency hatch 72 comprises a frame 74 which surrounds the discharge opening 58 and which cooperates with the inner partition 56 so as to obtain continuous surfaces. This frame 74 comprises a first wall 76 and a second wall 76 'approximately parallel to the longitudinal direction and a rear wall 783 in a transverse plane and a front wall 78' in another transverse plane. These walls 76, 76 ', 78, 78' form a duct which surrounds the discharge opening 58. This frame 74 is connected to the structure 52 of the aircraft by connecting elements 80, for example four legs of fixing shown in Figure 4.
    [0005] According to a feature of the invention, the emergency hatch 72 comprises: a fabric 84 with a first side 86 permanently connected to a first edge of the frame 74, a locking / unlocking mechanism 88, 88 'configured to hold OR not hooked a second side 90 of the fabric 84 (remote from the first side 86) to a second side of the frame 74. Thus, in the closed position, the fabric 84 is hooked and tensioned between the first and second walls of the frame 74 and closes the discharge opening 58. In the open position, said cloth 84 is no longer hooked and is suspended only at the first wall of the frame 74 and disengages the discharge opening 58.
    [0006] According to a configuration, the first wall of the frame 74 corresponds to the first wall 76 of the frame 74 and the second wall of the frame 74 corresponds to the second wall 76 'of the frame 74. According to one embodiment, the fabric 84 has a periphery square or rectangular approximately the same as the section of the discharge opening 58. By fabric is meant a fabric or flexible and deformable plastic member with a small thickness. Advantageously, the fabric 84 is elastic or comprises at least one elastic band so as to stretch when it is hooked and in the closed position. According to one embodiment, the first side 86 of the fabric 84 is connected to the frame 74 via a link which includes a hem at the first side 86 of the fabric 84 and a rod that is inserted into the fabric. hem, said rod comprising at each of its ends a tab connected by rivets or bolts to the frame 74. In a variant, the first side 86 of the fabric 84 is clamped between the frame 74 and a counterplate fixed to said frame by riveting or bolting. In FIGS. 4, 5A to 5D and 6, a first variant of the locking / unlocking mechanism 88 is illustrated. According to this variant, the locking / unlocking mechanism 88 comprises a rod 92 secured to the second side 90 of the fabric 84. said rod 92 having a hook 94 which cooperates with a keeper 96 secured to the frame 74 provided at the second wall 76 'of said frame 74. Preferably, the rod 92 has a length approximately equal to that of the second side 90 of the canvas 84.
    [0007] Thus, the locking / unlocking mechanism 88 is in the locked state and the fabric 84 is hooked when the hook 94 cooperates with the striker 96. It is in the unlocked state and the fabric 84 is no longer hooked when the hook 94 does not cooperate with the striker 96. The hook 94 is configured so that, when the rod 92 moves towards the inside of the cabin, said hook 94 disengages from the striker 96. Preferably, the hook 94 10 includes an end 98 which cooperates with the striker 96 and which is directed towards the emergency door 60 towards the outside of the aircraft. According to one embodiment, the hook 94 has an L shape, a first leg of the L being connected to the rod 92, the other leg of the L being configured to cooperate with the striker 96 and pointing towards the outside of the the plane.
    [0008] According to one embodiment, the striker 96 has a U-shape with two branches 100, 100 'parallel and spaced a distance sufficient to allow the passage of the hook 94 between them and a base 102 which has a bearing surface for the hook 94. The base 102 is shifted outwardly of the aircraft relative to the branches 100, 100 '. The branches 100, 100 'are connected to the frame 74 and the base 102 is spaced from the frame 74 so that the legs 100, 100', the base 102 and the frame 74 form an orifice through which the hook 94 passes. base 102 must be sufficiently spaced from the frame 74 to allow insertion or exit of the hook 94. As illustrated in FIG. 4, the frame 74 may comprise a cutout 104 to increase the distance between the frame 74 and the base 102.
    [0009] Advantageously, at least one stabilizing lug 106 is secured to the frame 74 to hold the fabric 84 in a plane allowing it to close the discharge opening 58 and limit the tilting of the rod 92 towards the emergency door 60 when the fabric 84 is hooked and the emergency hatch in the closed position. According to one embodiment, each stabilizing lug 106 has an L-shaped profile, one of the branches being secured to the frame 74, the other leg being in contact with the rod 92 and shifted outwardly of the aircraft relative to said rod 92 when the fabric 84 is hooked.
    [0010] Preferably, the hook 94 is positioned equidistant from the ends of the rod 92 and two stabilizing tabs 106, 106 'are provided close to each end of the rod 92. Thus, the stabilizing lugs 106, 106' limit the pivoting movements of the rod 92 with respect to the hook 94.
    [0011] The locking / unlocking mechanism 88 comprises a handle 108 (visible in FIGS. 5A to 5D) accessible from the booth 54 and a lever 110 positioned between the fabric 84 and the emergency door 60 so as to be actuated by the door of FIG. rescue 60 when it opens. According to one embodiment, the handle 108 comprises a first end 112 connected to the rod 92 and a second end 114 configured to be grasped by a person. The handle 108 extends from the rod 92 to the first side 86 of the fabric 84 and the interior of the cabin, forming an angle with the fabric 84, said angle being large enough to allow a person to grasp the lever 108 and pivoting it towards the web 84 so that the hook 94 disengages from the striker 96. Preferably, the handle 108 is perpendicular to the rod 92. According to one embodiment, the joystick 108 includes a bend 116 so that the second end 114 is substantially parallel to the web 84 in the locked state. According to one configuration, the handle 108 is disposed in the extension of the hook 94. According to one embodiment, the lever 110 comprises a first end 118 connected to the rod 92 and a second end 120 substantially parallel to the cloth 84 to the locked state. The lever 110 extends from the rod 92 to the first side 86 of the fabric 84 and the outside of the cabin. The second end 120 is spaced from the fabric 84 a distance such that the opening movement of the emergency door 60 causes the passage of the locking / unlocking mechanism 88 to the unlocked state. Preferably, the lever 110 is perpendicular to the rod 92. In one configuration, the lever 110 is connected to the rod 92 near the end of the rod 92 furthest from the pivot axis 70 of the door 60. As shown in Figure 5A, in the locked state, the fabric 84 is stretched and the hook 94 cooperates with the striker 96.
    [0012] To open the drain opening 58 from the inside of the booth, a person grasps the handle 108 and exerts a force toward the web 84 as shown in FIG. 5B. The rod 92 being held by the stabilizing tabs 106, 106 ', this action causes rotation of the rod 92 on itself. From a certain angle of rotation, the hook 94 no longer cooperates with the striker 96 and the locking / unlocking mechanism 88 goes to the unlocked state. Insofar as the fabric 84 is stretched when it is hooked, its elasticity favors the disengagement of the hook 96 and the passage of the emergency hatch in the open position, as illustrated in FIG. 5C. The fabric 84 is no longer hooked, it is suspended by its first side 86 and releases the discharge opening 58, as shown in Figure 5D. The presence of the rod 92 at the second side 90 allows the fabric 84 to hang substantially vertically.
    [0013] By following, the person can open the emergency door 60 by operating the inner opening control 66. To open the discharge opening 58 from the outside of the aircraft, the emergency door 60 is opened by operating the external opening control 68. From then on the emergency door 60 pivots towards the inside of the cabin. As illustrated in FIG. 6, the emergency door 60 presses the lever 110. The rod 92 being held by the stabilizing lug 106 'located at the other end of the rod 92 relative to the lever 110, the action of the emergency door 60 on the lever 110 causes a pivoting of the rod 92 relative to the stabilizing lug 106 '. From a certain pivoting angle, the hook 94 no longer cooperates with the striker 96 and the locking / unlocking mechanism 88 goes to the unlocked state. As the fabric 84 is no longer hooked, it is suspended by its first side 86 and disengages the discharge opening 58. In FIGS. 7, 8A to 8C and 9, a second variant of the locking / unlocking mechanism is illustrated. 88. As before, the locking / unlocking mechanism 88 'comprises a first rod 122 secured to the second side 90 of the fabric 84 which comprises a lever 124 operable from inside the cabin. Preferably, the first rod 122 has a length approximately equal to that of the second side 90 of the fabric 84. The lever 124 may be identical to the lever 108 of the first variant.
    [0014] The locking / unlocking mechanism 88 'comprises a second rod 126, parallel to the first rod 122, which is connected to the frame 74 via a pivotal connection allowing the second rod 126 to pivot on itself. According to one embodiment, the frame 74 comprises two supports 128, 128 'which comprise bearings 130, 130' in which are pivotally mounted the ends of the second rod 126. The second rod 126 comprises at least one hook 132, open towards the outside of the cabin, configured to retain the first rod 122. Advantageously, the second rod 126 5 comprises two hooks 132, 132 '. This configuration improves the stability of the first rod 122. According to one embodiment, the hooks 132, 132 'are as far apart as possible to enhance the stability of the first rod 122. The locking / unlocking mechanism 88' comprises a lever 134 having a first end connected to the second rod 126 and a second end facing the emergency door 60 operable by the emergency door 60 when it is opened. In one configuration, the hooks 132, 132 'are shifted inwardly of the car relative to the second shank 126. Therefore, the second shank 126 is shifted outwardly of the booth relative to the first shank 122. and in relation to the fabric 84. According to this configuration, the lever 134 extends perpendicular to the second shank 126 towards the first side 86 of the fabric 84, in a plane approximately parallel to the fabric 84. The second shank 126 is pivotally mounted relative to the supports 130, 130 'and occupies a holding position (visible in FIG. 7) in which the hooks 132, 132' retain the first rod 124 and a pivoted position (visible in FIG. 9) in which the hooks 132, 132 'no longer retain the first rod 124. Preferably, at least one torsion spring 136 is fitted at one end of the second rod 126 and positioned to hold the second rod 126 in the holding position. According to this configuration, to hang the fabric 84, it is necessary to use the lever 134 to position the second pivoting rod 126 in the rotated position, to stretch the fabric 84 to arrange the first rod 124 at the hooks 132, 132 ' then releasing the lever 134 so that the hooks 132, 132 'retain the first rod 124, as shown in Figure 8A. According to the second variant, to open the evacuation opening 58 from the inside of the cabin, a person grasps the lever 124 and exerts a force to move the first stem 124 towards the outside of the cabin as shown in FIG. 8B. After a certain stroke, the first rod 124 is no longer held by the hooks 132, 132 ', the locking / unlocking mechanism passes to the unlocked state. In the extent that the fabric 84 is stretched when hooked, its resilience promotes the disengagement of the first shaft 124 with the hooks 132, 132 'and the transition to the unlocked state as illustrated in FIG. 8B. As the fabric 84 is no longer hooked, it pivots, as illustrated in FIG. 8C, so as to disengage the discharge opening 58.
    [0015] To open the evacuation opening 58 from the outside of the aircraft, the emergency door 60 is opened by actuating the external opening control 68. As a result, the emergency door 60 pivots inwardly of the aircraft. cabin. As illustrated in FIG. 9, the emergency door 60 presses the lever 134. This action causes the second rod 126 to pivot on itself, against the torsion spring 136. In this position, the hooks 10 132, 132 'do not retain the first rod 124. Insofar as the fabric 84 is tensioned when it is hooked, its elasticity favors the exit of the first rod 124 from the hooks 132, 132'. The cloth 84 is no longer hooked, it pivots so as to clear the discharge opening 58. Of course, the invention is not limited to the embodiments described above.
    [0016] Thus, the emergency hatch 72 may not include a frame 74 which can then be replaced by the structure 52 of the aircraft or by any other element connected to said structure. Thus, whatever the embodiment, the first side 86 of the fabric 84, the striker 96, the stabilizing lugs 106, 106 ', the second rod 126 are connected directly to the structure 52 of the aircraft or indirectly to said structure 52 of the aircraft through at least one piece such as a frame 74.
    权利要求:
    Claims (8)
    [0001]
    REVENDICATIONS1. Aircraft cockpit comprising an outer skin (50) attached to a structure (52), an inner partition (56) defining the cabin, and an exhaust opening (58) extending through said outer skin (50) and said internal partition (56), said discharge opening (58) being closed by: an emergency door (60) articulated on the structure (52) between a closed position in which the emergency door (60) is disposed in the extending the outer skin (50) and closing off said discharge opening (58) and an open position in which the emergency door (60) pivots inwardly of the cabin, said emergency door (60) comprising means locking / unlocking device (64), an emergency hatch (72) movable between a closed position in which the emergency hatch (72) ensures the continuity of the interior partition (56) of the cabin and an open position, said hatch emergency device (72) comprising a mechanic locking / unlocking system (88, 88 '), characterized in that the emergency hatch (72) comprises a fabric (84) permanently connected to the structure (52) by a first side (86) and thereby that the locking / unlocking mechanism (88) comprises: a first part secured to a second side (90), opposite to the first side (86) and a second part integral with the structure (52), the first and second parts cooperating in the locked state so as to hook the second side (90) of the fabric (84) to the structure (52), and a rod (92, 122) secured to the second side (90) and a handle (108, 124 ) operable from the cab and connected to said rod (92, 122).
    [0002]
    2. Cockpit of an aircraft according to claim 1, characterized in that the fabric (84) is elastic or comprises at least one elastic band so that the fabric is stretched when it closes the opening of evacuation.
    [0003]
    3. Aircraft cockpit according to claim 1 or 2, characterized in that the first part of the locking / unlocking mechanism (88) comprises a hook (94) integral with the rod (92) and which cooperates with the second part comprising a striker (96).
    [0004]
    4. Control cabin of an aircraft according to one of claims 1 to 3, characterized in that the emergency door (72) comprises at least one stabilizing lug (106, 106 ') 3032420 13 integral with the structure ( 52), configured to limit the tilting of the rod (92) to the emergency door (60) when the fabric (84) closes the discharge opening (58).
    [0005]
    Aircraft cockpit according to one of claims 1 to 4, characterized in that the locking / unlocking mechanism (88) comprises a lever (110) which has a first end (118) connected to the rod (92) and a second end (120) facing the emergency door (60), said lever (110) being automatically actuated by said emergency door (60) when pivoted to the inside of the cabin.
    [0006]
    Aircraft cockpit according to claim 1, characterized in that the locking / unlocking mechanism (88 ') comprises a second rod (126) which comprises at least one hook (132, 132') configured to retaining the first rod (122), said second rod (126) being connected to the structure (52) via a pivotal connection so as to occupy a holding position in which the hook (132, 132 ') holds the first rod (124) and a rotated position in which the hook (132, 132 ') no longer holds the first rod (124). 15
    [0007]
    Aircraft cockpit according to claim 6, characterized in that the locking / unlocking mechanism (88 ') comprises at least one torsion spring (136) configured to hold the second rod (126) in position keeping.
    [0008]
    Aircraft cockpit according to claim 6 or 7, characterized in that the locking / unlocking mechanism (88 ') comprises a lever (134) having a first end connected to the second rod (126). and a second end facing the emergency door (60), said lever (134) being automatically operable by said emergency door (60) as it pivots inwardly of the cabin.
    类似技术:
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    同族专利:
    公开号 | 公开日
    CN105857566A|2016-08-17|
    EP3056424A1|2016-08-17|
    US9511846B2|2016-12-06|
    EP3056424B1|2017-09-13|
    FR3032420B1|2017-01-13|
    CN105857566B|2020-04-21|
    US20160236765A1|2016-08-18|
    引用文献:
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    EP3663191A1|2018-12-07|2020-06-10|Bombardier Inc.|Exterior handle position indicator for aircraft escape hatch|
    法律状态:
    2016-02-18| PLFP| Fee payment|Year of fee payment: 2 |
    2016-08-12| PLSC| Search report ready|Effective date: 20160812 |
    2017-02-17| PLFP| Fee payment|Year of fee payment: 3 |
    2018-11-30| ST| Notification of lapse|Effective date: 20181031 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1551100A|FR3032420B1|2015-02-11|2015-02-11|STEERING CABIN FOR AN AIRCRAFT EQUIPPED WITH EMERGENCY EVACUATION|FR1551100A| FR3032420B1|2015-02-11|2015-02-11|STEERING CABIN FOR AN AIRCRAFT EQUIPPED WITH EMERGENCY EVACUATION|
    EP16154297.2A| EP3056424B1|2015-02-11|2016-02-04|Aircraft cockpit provided with an emergency exit|
    CN201610082457.0A| CN105857566B|2015-02-11|2016-02-05|Aircraft cockpit equipped with a safety vent|
    US15/040,599| US9511846B2|2015-02-11|2016-02-10|Airplane flight deck equipped with an emergency escape|
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