A device for quickly unlocking emergency aircraft doors

Abstract

This utility model discloses a device for quickly unlocking an emergency hatch on an aircraft, comprising a housing and a cover plate. A plate is provided on one side of the cover plate, and a locking assembly is provided on the inner wall of the plate. The locking assembly includes sliding plates slidably connected to the inner walls on both sides of the plate. A rack is provided on one side of the sliding plate, and a protrusion is provided at the bottom of the sliding plate. A control lever is provided on the inner wall of the plate, and connecting shafts are provided on both sides of the control lever. Gears are sleeved on the outer walls of the connecting shafts, and the rack meshes with the gears. Protective shells are bolted to both sides of one side of the plate. This device utilizes the direct meshing of the rack and gears in the locking assembly. Simply rotating the connecting control lever causes the sliding plates to slide rapidly, instantly disengaging the protrusion from the groove and completing the unlocking process. This eliminates the complex linkage operations and tool dependence of traditional devices, achieving unlocking with only a single rotation of the connecting control lever. The operation logic is simple and intuitive, effectively avoiding unlocking delays caused by operational errors.

Description

Technical Field

[0001] This utility model relates to the field of aerospace mechanical design technology, specifically to a device for quickly unlocking an aircraft emergency hatch. Background Technology

[0002] During aircraft operation, emergency exits are critical components for ensuring personnel safety. Their ability to unlock quickly and reliably in emergencies directly impacts the lives of passengers and crew. Currently, traditional aircraft emergency exit unlocking devices often suffer from complex structures and cumbersome operations, requiring multiple steps or specific tools to unlock. In the event of a sudden accident, this can easily delay escape opportunities due to excessively long operation times.

[0003] However, traditional aircraft emergency exit unlocking devices, due to structural design limitations, struggle to meet the demands for rapid unlocking in emergency situations. Their unlocking process often involves the sequential operation of multiple interconnected components, sometimes requiring specialized tools, resulting in cumbersome and time-consuming actions. In sudden emergencies, this delay could potentially cause missed opportunities for optimal escape, posing a serious threat to personnel safety. Therefore, there is an urgent need to design a rapid unlocking device for aircraft emergency exits to address these issues. Utility Model Content

[0004] The purpose of this invention is to provide a device for quickly unlocking emergency hatches of aircraft, in order to overcome the aforementioned shortcomings in the prior art.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] A device for quickly unlocking an emergency hatch on an aircraft includes a housing and a cover plate. A plate body is provided on one side of the cover plate, and a locking assembly is provided on the inner wall of the plate body. The locking assembly includes sliding plates slidably connected to the inner walls on both sides of the plate body. A rack is provided on one side of the sliding plate, and a protrusion is provided on the bottom of the sliding plate.

[0007] The inner wall of the plate is provided with a control lever, and both sides of the control lever are provided with connecting control levers. Gears are sleeved on the outer wall of the connecting control levers. The rack meshes with the gears. Protective shells are bolted to both sides of one side of the plate.

[0008] Preferably, the inner wall of the housing is provided with grooves on both sides, and the grooves are in clearance fit with the protrusions.

[0009] Preferably, both sides of the plate are provided with opening and closing components. The opening and closing components include a second fixing plate bolted to one side of the plate, a first fixing plate on the top inner wall of the shell, a first hinge on the inner wall of the first fixing plate, and a second hinge on the outer wall of the first fixing plate.

[0010] Preferably, the inner wall of the fixing plate two is provided with hinge three and hinge four respectively. The middle part of hinge one is connected to hinge three, the lower part of the middle part of hinge one is connected to hinge four, and the bottom end of hinge two is connected to hinge three.

[0011] Preferably, a rotary control lever is provided on both inner walls of the housing, and a telescopic rod is rotatably connected to the outer wall of the rotary control lever. The output control lever of the telescopic rod is connected to the bottom end of the hinge, and a return spring is sleeved on the outer wall of the output control lever of the telescopic rod.

[0012] Preferably, the outer wall of the connecting control lever is provided with an anti-slip grip, and the outer wall of the anti-slip grip is provided with uniformly distributed anti-slip texture.

[0013] In the above technical solution, the present invention provides a device for quickly unlocking an aircraft emergency hatch, which has the following advantages:

[0014] (1) This device uses the direct meshing of the rack and pinion in the locking assembly to drive the sliding plate to slide quickly by simply rotating the connecting lever, so that the protrusion can be instantly disengaged from the groove to complete the unlocking. Compared with the multi-step operation of traditional devices, the unlocking time is greatly shortened, and "one-click" quick unlocking can be achieved in emergency situations, buying critical time for personnel to escape.

[0015] (2) It eliminates the complex linkage operations and tool dependence of traditional devices, and unlocking can be completed by simply rotating a connecting joystick. The operation logic is simple and intuitive. Even in a tense and chaotic emergency, the operation method can be quickly mastered, effectively avoiding unlocking delays caused by operational errors. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this utility model. For those skilled in the art, other drawings can be obtained based on these drawings.

[0017] Figure 1 This is an exploded structural diagram of an embodiment of a rapid unlocking aircraft emergency hatch device according to the present invention.

[0018] Figure 2 This is a perspective view of the opening and closing component structure provided in an embodiment of a quick-unlocking aircraft emergency hatch device according to the present invention.

[0019] Figure 3 This is a perspective view of the shell structure of an embodiment of a quick-unlocking emergency hatch device for an aircraft according to the present invention.

[0020] Figure 4 This is a perspective view of the locking component structure provided in an embodiment of a quick-unlocking aircraft emergency hatch device according to the present invention.

[0021] 1. Housing; 2. Groove; 3. Cover plate; 4. Plate; 5. Opening and closing assembly; 51. Fixing plate one; 52. Fixing plate two; 53. Hinge one; 54. Hinge two; 55. Hinge three; 56. Hinge four; 57. Rotating shaft; 58. Telescopic rod; 59. Return spring; 6. Locking assembly; 61. Sliding plate; 62. Rack; 63. Protrusion; 64. Control lever; 65. Connecting shaft; 66. Gear; 67. Protective shell. Detailed Implementation

[0022] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be further described in detail below with reference to the accompanying drawings.

[0023] like Figure 1-4 As shown, the present invention provides a quick-unlocking aircraft emergency hatch device, including a housing 1 and a cover plate 3. A plate body 4 is provided on one side of the cover plate 3, and a locking component 6 is provided on the inner wall of the plate body 4. The locking component 6 includes a sliding plate 61 slidably connected to the inner walls on both sides of the plate body 4. A rack 62 is provided on one side of the sliding plate 61, and a protrusion 63 is provided at the bottom of the sliding plate 61.

[0024] The inner wall of the plate 4 is provided with a control lever 64, and both sides of the control lever 64 are provided with connecting shafts 65. Gears 66 are sleeved on the outer wall of the connecting shafts 65. The rack 62 meshes with the gears 66. Protective shells 67 are bolted to both sides of one side of the plate 4.

[0025] In this embodiment, it includes a housing 1 and a cover plate 3. The housing 1 and the cover plate 3 are connected by an opening and closing component 5 to achieve controllable rotation, and at the same time, a locking component 6 completes the stable locking of the closed state.

[0026] A plate body 4 is provided on one side of the cover plate 3. A locking component 6 is provided on the inner wall of the plate body 4. The locking component 6 includes a sliding plate 61 that is slidably connected to the inner walls on both sides of the plate body 4. The plate body 4 is integrally formed on one side of the cover plate 3. The plate body 4 has a rectangular frame structure and two horizontal sliding grooves are symmetrically opened on its inner side wall. The sliding plate 61 of the locking component 6 is slidably connected to the plate body 4 through the sliding grooves to ensure that the sliding plate 61 can move smoothly back and forth in the horizontal direction.

[0027] A rack 62 is provided on one side of the sliding plate 61. The rack 62 is fixed to the side surface of the sliding plate 61 facing the center of the plate body 4 by welding. The tooth surface of the rack 62 faces the outside of the plate body 4. A protrusion 63 is provided at the bottom of the sliding plate 61. The bottom of the sliding plate 61 is integrally formed with a protrusion 63. The cross section of the protrusion 63 is rectangular.

[0028] The inner wall of the plate 4 is provided with a control lever 64. The control lever 64 is located in the middle of the plate 4. Both ends are connected to the plate 4 through connecting shafts 65. Both sides of the control lever 64 are provided with connecting shafts 65. The connecting shafts 65 are rotatably connected to the plate 4 to ensure the rotation of the gear 66.

[0029] Gears 66 are sleeved on the outer wall of the connecting shaft 65. The outer wall of the rod segment of the connecting shaft 65 located outside the plate 4 is connected by a key to the gears 66. The rack 62 meshes with the gears 66. When the connecting shaft 65 drives the gears 66 to rotate, the sliding plates 61 on both sides can be driven to move synchronously in opposite directions through inter-gear transmission.

[0030] Protective shells 67 are bolted to both sides of one side of the plate 4. The protective shells 67 are rectangular structures and are connected to the plate 4 through the bolts, which have grooves to ensure that dust is blocked from entering the meshing area of ​​the gears 66 and racks 62.

[0031] Specifically, grooves 2 are provided on both sides of the inner wall of the housing 1. The grooves 2 are in clearance fit with the protrusions 63. Grooves 2 are provided on both sides of the inner wall of the housing 1 corresponding to the positions of the protrusions 63. The cross-sectional shape of the grooves 2 is adapted to the protrusions 63, and a clearance fit of 0.5-1mm is maintained between the two.

[0032] When the cover plate 3 is closed, the protrusion 63 can be fully embedded in the groove 2, and the cover plate 3 and the housing 1 are initially locked through the mechanical engagement of the two; when the protrusion 63 is removed from the groove 2, the cover plate 3 can be released from the locked state.

[0033] Specifically, opening and closing components 5 are provided on both sides of the plate body 4. The opening and closing components 5 include a second fixing plate 52 bolted to one side of the plate body 4 and a first fixing plate 51 provided on the top inner wall of the shell 1. The opening and closing components 5 are symmetrically arranged at the edges of both sides of the plate body 4. Each set of opening and closing components 5 includes a second fixing plate 52 bolted to the side surface of the plate body 4 and a first fixing plate 51 welded to the top inner wall of the shell 1.

[0034] The inner wall of the fixing plate 51 is provided with hinge 53, and the outer wall of the fixing plate 51 is provided with hinge 54. The fixing plate 51 has an "L" shaped structure. The inner wall of its vertical section is connected to hinge 53 by a pin, and the outer wall of its horizontal section is connected to hinge 54 by a pin.

[0035] Furthermore, the inner wall of the second fixed plate 52 is provided with hinge 3 55 and hinge 4 56 respectively. The upper and lower positions of the inner wall of the second fixed plate 52 are connected to hinge 3 55 and hinge 4 56 respectively by pins. The middle part of hinge 1 53 is connected to hinge 3 55, the lower part of the middle of hinge 1 53 is connected to hinge 4 56, and the bottom end of hinge 2 54 is connected to hinge 3 55. The middle node of hinge 1 53 is hinged to one end of hinge 3 55, the lower part of the middle of hinge 1 53 is hinged to one end of hinge 4 56, and the bottom end of hinge 2 54 is hinged to the middle node of hinge 3 55, forming a multi-link linkage structure.

[0036] Furthermore, a pivot 57 is provided on both inner walls of the housing 1. In order to realize the automatic reset function, a pivot 57 is welded on both inner walls of the housing 1 corresponding to the position of the opening and closing component 5. A telescopic rod 58 is rotatably connected to the outer wall of the pivot 57. The output end of the telescopic rod 58 is connected to the bottom end of the hinge 53. A reset spring 59 is sleeved on the outer wall of the output end of the telescopic rod 58. The output end of the telescopic rod 58 is connected to the bottom end of the hinge 53 through a ball joint, and a reset spring 59 is sleeved on the outer wall of its output rod.

[0037] One end of the return spring 59 abuts against the cylinder end of the telescopic rod 58, and the other end abuts against the limiting ring of the output rod. When the cover plate 3 is opened, the return spring 59 is compressed and stores elastic potential energy, providing power for the automatic closing of the cover plate 3.

[0038] Furthermore, the outer wall of the control lever 64 is provided with an anti-slip grip, and the outer wall of the anti-slip grip is provided with evenly distributed anti-slip textures. The outer wall of the grip end of the control lever 64 is covered with an anti-slip grip made of rubber, and the surface of the grip is pressed with evenly distributed diagonal anti-slip textures, which can effectively increase the friction during operation and prevent the hand from slipping and affecting the stability of the locking operation.

[0039] Working steps: 1. When the emergency hatch is closed, the protrusion 63 of the sliding plate 61 in the locking assembly 6 is engaged with the groove 2 of the housing 1, and the gear 66 and the rack 62 are meshed and fixed.

[0040] 2. When the opening and closing assembly 5 is stationary, the telescopic rod 58 is not activated, the return spring 59 retracts naturally, and the cover plate 3 is tightly fitted to the housing 1;

[0041] 3. When unlocking is required, hold the non-slip handle of the control lever 64, and use the non-slip texture to hold it firmly. Turn the control lever 64 to drive the connecting shaft 65 and the gears 66 on both sides to rotate.

[0042] Fourth, gear 66 meshes with rack 62, driving sliding plate 61 to slide within plate 4, causing protrusion 63 to disengage from groove 2, thus completing the unlocking process;

[0043] 5. After unlocking, the reset spring 59 pushes out the telescopic rod 58, and its output end extends to push the hinge 1 53. The hinge 1 53 is linked with the hinge 3 55 and the hinge 4 56, and the hinge 2 54 assists in the transmission, driving the plate 4 and the cover plate 3 to open.

[0044] 6. When the hatch is reset, manually pull the control lever 64. When the cover plate 3 is in contact with the shell 1, rotate the connecting shaft 65 in the opposite direction. The gear 66 drives the rack 62 in the opposite direction, so that the sliding plate 61 is reset and the protrusion 63 is locked back into the groove 2.

[0045] The above description only illustrates certain exemplary embodiments of the present invention. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. A quick release aircraft emergency hatch door device comprising a housing (1) and a cover plate (3), characterized in that, A plate body (4) is provided on one side of the cover plate (3), and a locking assembly (6) is provided on the inner wall of the plate body (4). The locking assembly (6) includes a sliding plate (61) slidably connected to the inner walls of both sides of the plate body (4). A rack (62) is provided on one side of the sliding plate (61), and a protrusion (63) is provided at the bottom of the sliding plate (61). The inner wall of the plate (4) is provided with a control lever (64), and both sides of the control lever (64) are provided with connecting shafts (65). The outer wall of the connecting shafts (65) is fitted with gears (66). The rack (62) meshes with the gears (66). The plate (4) is bolted to both sides on one side with a protective shell (67).

2. A quick release aircraft emergency hatch door assembly according to claim 1, wherein, The inner wall of the housing (1) is provided with grooves (2) on both sides, and the grooves (2) are in clearance fit with the protrusions (63).

3. A quick release aircraft emergency hatch door assembly according to claim 1, wherein, Both sides of the plate (4) are provided with opening and closing components (5). The opening and closing components (5) include a fixing plate two (52) bolted to one side of the plate (4). The top inner wall of the shell (1) is provided with a fixing plate one (51). The inner wall of the fixing plate one (51) is provided with a hinge one (53). The outer wall of the fixing plate one (51) is provided with a hinge two (54).

4. A quick release aircraft emergency hatch door assembly according to claim 3, wherein, The inner wall of the fixed plate 2 (52) is provided with hinge 3 (55) and hinge 4 (56). The middle part of hinge 1 (53) is connected to hinge 3 (55), the lower part of the middle part of hinge 1 (53) is connected to hinge 4 (56), and the bottom end of hinge 2 (54) is connected to hinge 3 (55).

5. A quick release aircraft emergency hatch door assembly according to claim 4, wherein, The inner walls of both sides of the housing (1) are provided with a rotating shaft (57). The outer wall of the rotating shaft (57) is rotatably connected to a telescopic rod (58). The output end of the telescopic rod (58) is connected to the bottom end of the hinge (53). A return spring (59) is sleeved on the outer wall of the output end of the telescopic rod (58).

6. A quick unlock aircraft emergency hatch door device according to claim 1, characterized in that, The outer wall of the control lever (64) is provided with an anti-slip grip, and the outer wall of the anti-slip grip is provided with uniformly distributed anti-slip texture.

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