Mounting structure of full-view cabin door of helicopter

Abstract

The invention provides a mounting structure of a full-view cabin door of a helicopter, and belongs to the technical field of helicopters.The mounting structure specifically comprises a mounting frame located on a helicopter body, a cabin door outer frame and a sliding frame, the sliding frame is slidably mounted on the inner side wall of a cockpit, and a connecting frame is fixed to the cabin door outer frame and hinged to the sliding frame; a limiting plate abutting against the inner side face of the mounting frame is arranged on the connecting frame, and a door lock is arranged on the other side of the cabin door outer frame. The full-view cabin door is rotated until the cabin door outer frame abuts against the first abutting edge, the limiting rod penetrates through the through groove, the cabin door outer frame is pushed to enable the hinge point of the sliding frame and the connecting frame to move towards the outer side of the area defined by the mounting frame, and the full-view cabin door is in a closed state. The limiting plate abuts against the inner side wall of the mounting frame, the limiting rod abuts against the inner side of the first abutting edge, and the inner side faces of the top and the bottom of the cabin door outer frame abut against the outer side of the first abutting edge. According to the treatment scheme, the stability when the full-view cabin door is closed is improved.

Description

Technical Field

[0001] This application relates to the field of helicopters, and in particular to an installation structure for a helicopter full-view cabin door. Background Technology

[0002] In helicopter design, the visibility performance of the cockpit and mission cabin directly affects flight safety and operational efficiency. This is especially true in specialized operations such as search and rescue, reconnaissance, and power line inspection, where operators have an increasingly urgent need for omnidirectional visibility. To meet this need, omnidirectional hatches have emerged. These hatches utilize large, outward-protruding arc-shaped or curved transparent windows to effectively reduce blind spots and significantly improve the visibility of the surrounding environment for personnel inside the cabin.

[0003] However, the unique structure of the full-view hatch also presents challenges to its installation and stability. Existing full-view hatches mostly use traditional hinges: although the hinge structure can allow the hatch to be opened by rotation, it is only fixed by a single hinge axis and door lock when closed. Because the transparent viewing window protrudes outward, the overall center of gravity of the hatch shifts outward. Moreover, when the helicopter is impacted by airflow during flight, the protruding hatch is prone to swaying along the hinge axis, which may lead to structural fatigue and other problems after long-term use. Therefore, optimizing the installation structure of the cabin door, improving its stability when closed, and reducing the shaking caused by airflow impact, while ensuring the full field of vision function, has become a key technical challenge that urgently needs to be addressed in the design of full field of vision helicopter cabin doors. Summary of the Invention

[0004] In view of this, this application provides an installation structure for a helicopter full-view cabin door, which solves the problem that the full-view cabin door is easily shaken by the large airflow impact in the prior art, and improves the stability of the full-view cabin door when it is closed.

[0005] The installation structure for a helicopter full-view cabin door provided in this application adopts the following technical solution: A mounting structure for a helicopter full-view cabin door includes a mounting frame, a cabin door outer frame, and a sliding bracket located on the fuselage. The mounting frame is used to mount the cabin door outer frame. The sliding bracket is slidably mounted on the inner side wall of the cockpit and slides along the fore-and-aft direction of the helicopter. The sliding bracket is located on either the nose or tail side of the helicopter corresponding to the mounting frame. A connecting bracket is fixed to one side of the cabin door outer frame. One side of the connecting bracket extends into the fuselage and is hinged to the sliding bracket. A limiting plate is provided on the connecting bracket that abuts against the inner side of the mounting frame. A door lock is provided on the other side of the cabin door outer frame. The door lock and the other side of the helicopter corresponding to the nose or tail of the mounting frame cooperate to limit the closed state of the cabin door. The mounting frame has a first abutting edge on its upper and lower sides that abuts against the upper and lower sides of the hatch outer frame. The inner sides of the top and bottom of the hatch outer frame are provided with limiting rods. The limiting rods and the portion of the hatch outer frame that abuts against the first abutting edge are spaced apart. The first abutting edge is provided with a through groove for the limiting rods to pass through. When the full-view hatch is in the open state, the hinge points of the sliding frame and the connecting frame are located within the area enclosed by the mounting frame; rotate the full-view hatch until the hatch outer frame abuts against the first abutment edge and the limiting rod passes through the through groove, push the hatch outer frame to move the hinge points of the sliding frame and the connecting frame outwards from the area enclosed by the mounting frame, so that the full-view hatch is in the closed state, the limiting plate abuts against the inner wall of the mounting frame, the limiting rod and the inner side of the first abutment edge abut against each other, and the inner sides of the top and bottom of the hatch outer frame abut against the outer side of the first abutment edge.

[0006] Optionally, the inner sidewall of the cockpit is provided with a slide rail, and the slide rail is provided with a slider. The slide rail and the slider are detachably connected.

[0007] Optionally, the end of the slide rail away from the hinge point of the sliding frame is provided with a fixed plate, the side of the slider facing the fixed plate is provided with a slide rod, the fixed plate is provided with a hole for the slide rod to pass through, and a spring is sleeved on the outer periphery of the slide rod between the fixed plate and the slider. When the full-view hatch is in the closed state, the spring is in the compressed state.

[0008] Optionally, the door lock includes a cam and a handle that are rotatably mounted on the outer frame of the hatch. The axial direction of the cam's rotation axis is set along the wall thickness direction of the full-view hatch. The handle and the cam are fixedly connected. The handle drives the cam to rotate. A mating block is provided on the inner side wall of the mounting frame that mates with the door lock. The mating block has a groove for the distal end of the cam to extend into. A straight line passing through the cam axis and parallel to the sliding direction of the sliding frame is a first straight line. When the full-view hatch is closed, the angle between the line connecting the distal end of the cam and the cam axis and the first straight line is -0°. The distal end of the cam abuts against the bottom of the groove and simultaneously abuts against the top or bottom wall of the groove. During the process of the distal end of the cam rotating from the groove opening to the extreme position inside the groove, the distal end of the cam passes through the first straight line.

[0009] Optionally, the mounting frame has a second abutting edge on the side away from the sliding frame, and when the full-view hatch is in the closed state, the side of the hatch outer frame with the door lock abuts against the second abutting edge.

[0010] Optionally, the mounting frame is coated with a self-lubricating coating on the side surface corresponding to the first abutment edge and the second abutment edge, and on the inner surface of the mounting frame corresponding to the limiting plate. The area of ​​the hatch outer frame abutting the first abutment edge and the second abutment edge, as well as the side of the limiting plate facing the mounting frame, are provided with sealing strips, and the inner edge of the side of the mounting frame corresponding to the limiting plate is rounded.

[0011] Optionally, the sliding bracket is located on one side of the mounting frame corresponding to the nose of the helicopter, the door lock is located on one side of the outer frame of the cabin door corresponding to the tail, the handle includes a connecting column and a grip, the connecting column is connected to the cam, one end of the grip is connected to the connecting column, and the other end of the grip is a free end. When the grip is rotated so that the free end moves closer to the nose, the distal end of the cam rotates from the range of the full-view cabin door into the groove. When the grip is rotated so that the free end moves closer to the tail, the distal end of the cam rotates out of the groove.

[0012] Optionally, the grip may be provided with anti-slip texture or arc-shaped raised structure.

[0013] In summary, this application includes the following beneficial technical effects: When the full-view hatch is closed, the limiting plate abuts against the inner wall of the mounting frame, the limiting rod abuts against the inner side of the first abutting edge, and the inner sides of the top and bottom of the hatch outer frame abut against the outer side of the first abutting edge. In this application, the abutment between the limiting plate and the mounting frame, as well as the double-sided abutment between the hatch outer frame and the abutting piece on the mounting frame, improve the stability of the full-view hatch when it is closed, and improve the problem of large internal and external swaying caused by the outward protrusion of the full-view hatch due to the large airflow influence during helicopter flight. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 A schematic diagram of the outer structure of the helicopter's all-view cabin door; Figure 2 This is a schematic diagram of the installation structure when the helicopter's full-view cabin door is closed and locked. Figure 3 This is a schematic diagram of the installation structure when the helicopter's all-view cabin door is closed and locked. Figure 4This is a schematic diagram of the installation structure when the helicopter's all-view cabin door is open, as per this application. Figure 5 This is a schematic diagram of the mating structure of the sliding frame, the hatch outer frame, and the connecting frame in this application; Figure 6 This is a schematic diagram of the installation structure when the helicopter's full-view cabin door is half-open.

[0016] Explanation of reference numerals in the attached drawings: 1. Mounting frame; 11. First abutment edge; 12. Second abutment edge; 13. Through groove; 14. Clearance notch; 2. Outer frame of hatch; 21. Limiting rod; 22. Transparent viewing window; 3. Sliding frame; 31. Crossbar; 32. U-shaped frame; 33. Main body section; 4. Slide rail; 41. Slider; 42. Fixing plate; 43. Slide rod; 44. Spring; 5. Connecting frame; 51. Limiting plate; 52. Connecting plate; 53. Hinge seat; 6. Door lock; 61. Cam; 62. Handle; 63. Mating block; 64. Groove. Detailed Implementation

[0017] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0018] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0019] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0020] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The illustrations only show the components related to this application and are not drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0021] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0022] This application provides an installation structure for a helicopter full-view cabin door.

[0023] like Figure 1 and Figure 2 As shown, a helicopter full-view cabin door installation structure includes a mounting frame 1, a cabin door outer frame 2, and a sliding bracket 3 located on the fuselage. A transparent viewing window 22 protruding outward is installed on the inner side of the cabin door outer frame 2.

[0024] The mounting frame 1 is used to install the cabin door outer frame 2. The sliding bracket 3 is slidably installed on the inner side wall of the cockpit. The sliding bracket 3 slides along the front-rear direction of the helicopter and is located on either the nose or tail side of the helicopter corresponding to the mounting frame 1. A connecting bracket 5 is fixed on one side of the cabin door outer frame 2. One side of the connecting bracket 5 extends into the fuselage and is hinged to the sliding bracket 3. The connecting bracket 5 is provided with a limiting plate 51 that abuts against the inner side of the mounting frame 1. A door lock 6 is provided on the other side of the cabin door outer frame 2. The door lock 6 and the other side of the helicopter corresponding to the mounting frame 1, the nose or tail side, cooperate to limit the closed state of the cabin door.

[0025] like Figure 2 and Figure 3 As shown, the upper and lower sides of the mounting frame 1 are provided with first abutting edges 11 that abut against the upper and lower sides of the hatch outer frame 2. The inner sides of the top and bottom of the hatch outer frame 2 are provided with limiting rods 21. The limiting rods 21 are fixed on the hatch outer frame 2. The limiting rods 21 and the portion of the hatch outer frame 2 that abut against the first abutting edges 11 are spaced apart. The first abutting edge 11 is provided with a through groove 13 for the limiting rods 21 to pass through.

[0026] like Figure 2 , Figure 3 and Figure 4As shown, when the full-view hatch is in the open state, the hinge point of the sliding frame 3 and the connecting frame 5 is located within the area enclosed by the mounting frame 1. At this time, the hatch outer frame 2 can rotate around the sliding frame 3, realizing the free rotation of the full-view hatch. Rotate the full-view hatch until the hatch outer frame 2 abuts against the first abutment edge 11 and the limiting rod 21 passes through the through groove 13, pushing the hatch outer frame 2 to move the hinge point of the sliding frame 3 and the connecting frame 5 to the outside of the area enclosed by the mounting frame 1, so that the full-view hatch is in the closed state. At this time, the limiting plate 51 In this application, the inner side of the mounting frame 1 is abutted by the limiting plate 51, the inner side of the limiting rod 21 and the first abutting edge 11 are abutted by the limiting plate 51, the inner side of the limit rod 21 and the first abutting edge 11 are abutted by the limit rod 51, and the outer side of the door frame 2 and the abutting edge on the mounting frame 1 are abutted by the limit rod 51. This improves the stability of the full-view door when it is closed and improves the problem of large internal and external swaying caused by the outward protrusion of the full-view door due to the large airflow influence during helicopter flight.

[0027] In one embodiment, the limiting rod 21 is cylindrical, and the arc-shaped outer peripheral surface of the limiting rod is used to abut against the inner side of the mounting frame 1, so that the limiting rod 21 can overlap and abut against the first abutting edge 11 when the hatch slides.

[0028] The inner sidewall of the cockpit is provided with a slide rail 4, and a slider 41 is provided on the slide rail 4. The sliding frame 3 and the slider 41 are detachably connected. In this embodiment, two spaced slide rails 4 are provided on the inner wall of the helicopter cockpit fuselage. The slide rails 4 are located on the fuselage sidewall between the mounting frame 1 and the nose. The sliding frame 3 includes two crossbars 31 corresponding to the two slide rails 4. The two crossbars 31 can also be connected by a vertical bar to improve the stability and synchronization of the sliding frame 3. The slide rails 4 and sliders 41 are purchased as a set. Generally, the two ends of the slide rails 4 have limiting mechanisms to prevent the sliders 41 from slipping. The specific structure is purchased according to requirements and will not be described in detail here.

[0029] In the embodiment of this application, when the full-view hatch is closed, the side of the hatch outer frame 2 that mounts the connecting bracket 5 abuts against the side of the corresponding sliding bracket 3 of the mounting frame 1.

[0030] like Figure 2 , Figure 3 and Figure 5 As shown, the more specific structural descriptions of the connecting frame 5 and the sliding frame 3 are as follows: In one embodiment, the connecting frame 5 includes a mounting plate and hinge seats 53 at both ends of the mounting plate. The height range of the mounting plate is within the range enclosed by the mounting frame 1. The hinge seats 53 of the mounting plate are hinged to the crossbar 31. The hinge axis is set along the height direction of the fuselage. The mounting plate includes a connecting plate 52 connected to the outer frame of the hatch and the limiting plate 51. In order to avoid the crossbar 31 interfering with the rotation of the outer frame of the hatch and the connecting frame 5, the crossbar 31 includes a main body section 33 and a hinge section. The main body section 33 is fixedly connected by bolts and sliders. The hinge section is designed as a U-shaped frame 32. The opening of the U-shaped frame 32 faces the outside of the fuselage. One end of the U-shaped frame 32 is fixedly connected to the main body section 33. The other end of the U-shaped frame 32 is hinged to the hinge seat 53. The internal area of ​​the U-shaped frame 32 provides sufficient space for the rotation of the outer frame of the hatch and the connecting frame 5. The hinge seat 53 extends outward from the mounting plate in a direction perpendicular to the mounting plate.

[0031] The slide rail 4 has a fixed plate 42 at the end away from the hinge point of the sliding frame 3. The slider 41 has a slide rod 43 on the side facing the fixed plate 42. The fixed plate 42 has a hole for the slide rod 43 to pass through. A spring 44 is sleeved on the outer periphery of the slide rod 43 between the fixed plate 42 and the slider 41. The two ends of the spring 44 only contact the fixed plate 42 and the slider 41. There is no substantial connection structure between the spring 44 and the fixed plate 42, or between the spring 44 and the slider 41. This avoids the need to overcome the tensile force of the spring 44 when opening the door. When the full-view hatch is closed, the spring 44 is in a compressed state. This application does not limit whether the spring 44 is in a compressed state when the hatch needs to be rotated to open. However, as an embodiment, when the hatch can be rotated to the maximum opening angle, the spring 44 is in a natural state, and the length of the spring 44 is less than the distance between the opposite sides of the slider 41 and the fixed plate 42 at this time. That is, in this embodiment, the spring 44 only provides assistance for the sliding of the hatch in the initial stage of opening, and does not provide assistance throughout the entire sliding stage. This design ensures that the hatch is not subject to the resistance of the spring 44 in the early stage of sliding during the closing process, and only needs to overcome the elastic force of the spring 44 in the later stage to compress the spring 44. When the length of the slider 43 needs to be slid to the limit position, the slider 43 is still inserted on the fixed plate 42.

[0032] In one embodiment, a protective shell is provided on the inner wall of the cockpit, covering the outer periphery of the slide rail 4, the slider 41 and the sliding frame 3, and a channel is provided on the side wall of the protective shell through which the sliding frame 3 passes.

[0033] like Figure 2 , Figure 5 and Figure 6As shown, in one embodiment, the first abutting edge 11 is provided with a clearance notch 14 on the side near the sliding frame 3. The upper and lower top ends of the hatch outer frame 2 pass through the clearance notch 14 on the side near the sliding frame 3 during the rotation to open. The design of the clearance notch 14 avoids the interference of the first abutting edge 11 on the mounting frame 1 with the rotation of the hatch outer frame.

[0034] like Figure 1 , Figure 2 and Figure 3 As shown, the door lock 6 includes a cam 61 and a handle 62 rotatably mounted on the outer frame 2 of the hatch. Handles 62 are provided on both the inner and outer sides of the outer frame 2. The axial direction of the cam 61's rotation axis is along the wall thickness direction of the full-view hatch. The handle 62 and the cam 61 are fixedly connected. The handle 62 drives the cam 61 to rotate. A mating block 63 is provided on the inner side wall of the mounting frame 1 that mates with the door lock 6. The mating block 63 has a groove 64 for the distal end of the cam 61 to extend into. A straight line parallel to the sliding direction of the sliding frame 3 and centered on cam 61 is the first straight line. When the full-view hatch is closed, the angle between the line connecting the farthest point of cam 61 and the axis of cam 61 and the first straight line is 5-20°. The far end of cam 61 abuts against the bottom of the groove 64 and simultaneously abuts against the top or bottom wall of the groove 64. During the process of the far end of cam 61 rotating from the opening of the groove 64 to its limit position within the groove 64, the far end of cam 61 passes through the first straight line. When the full-view hatch is closed, cam 61 is tilted relative to the sliding direction of the hatch. Under the action of spring 44, cam 61 has a tendency to continue rotating, but the far end of cam 61 is restricted by the inner wall of the groove 64, thereby stabilizing the position of cam 61 and achieving the function of locking handle 62 when the full-view hatch is closed. In one embodiment, cam 61 is located outside groove 64, allowing the full-view hatch to rotate. The distal end of cam 61 faces downward. When the full-view hatch contacts the first abutment edge 11 of mounting frame 1, rotating handle 62 drives cam 61 to rotate. The distal end of cam 61 enters groove 64 and rotates upward. After passing through the first straight line, it abuts the top wall of groove 64 in an inclined state. During this process, as cam 61 rotates, the cam 61 abuts the inner wall of groove 64, gradually pushing the hatch outer frame 2 towards the sliding frame 3 to compress spring 44 until the hatch outer frame 2 reaches its limit position. At this time, the distal end of cam 61 is located above the first straight line. Under the action of spring 44, the hatch outer frame 2 has a tendency to move towards door lock 6, causing the distal end of cam 61 to continue to move upward. However, cam 61 cannot continue to rotate at the limit line on the top wall of groove 64. Under natural conditions, the distal end of cam 61 will not fall downward, causing door lock 6 to fail.

[0035] In one embodiment, a protective cover is provided on the inner side of the hatch frame 2, which covers the outer periphery of the cam 61, and the protective cover is provided with a channel for the cam 61 to rotate.

[0036] like Figure 1 and Figure 2 As shown, the mounting frame 1 has a second abutment edge 12 on the side away from the sliding frame 3. When the full-view hatch is closed, the side of the hatch outer frame 2 with the door lock 6 abuts against the second abutment edge 12. The width of the second abutment edge 12 covers the sliding range of the hatch outer frame 2 away from the sliding frame 3 during the locking process, ensuring the sealing of the hatch when closed.

[0037] The mounting frame 1 is coated with a self-lubricating coating on the side surfaces corresponding to the first abutment edge 11 and the second abutment edge 12, and on the inner surface of the mounting frame 1 corresponding to the limiting plate 51. Sealing strips are provided on the area of ​​the hatch outer frame 2 abutting the first abutment edge 11 and the second abutment edge 12, and on the side of the limiting plate 51 facing the mounting frame 1. In this embodiment, the self-lubricating coating is Teflon. This ensures a seal while preventing wear and damage to the sealing strips. The inner corner of the side of the mounting frame 1 corresponding to the limiting plate 51 is rounded, which guides the limiting plate 51 when it begins to contact the mounting frame 1 when the hatch is closed, ensuring smooth closure of the hatch.

[0038] The sliding frame 3 is located on the side of the mounting frame 1 corresponding to the nose of the helicopter, and the door lock 6 is located on the side of the outer frame 2 of the cabin door corresponding to the tail. The handle 62 includes a connecting column and a grip. The connecting column is connected to the cam 61. One end of the grip is connected to the connecting column, and the other end of the grip is a free end. When the grip is rotated so that the free end moves closer to the nose, the distal end of the cam 61 rotates from the range of the full-view cabin door into the groove 64. When the grip is rotated so that the free end moves closer to the tail, the distal end of the cam 61 rotates out of the groove 64. When the door lock 6 is opened and closed, the force exerted by the personnel on the handle 62 is consistent with the sliding direction of the full-view cabin door.

[0039] In this embodiment, when the full-view cabin door is closed, the free end of the handle faces the nose of the aircraft, and the distal end of the cam 61 faces the tail and is located in the groove 64. When the full-view cabin door is open, the free end of the handle faces upwards of the aircraft, and the distal end of the cam 61 faces downwards of the aircraft, ensuring that both the handle and the cam 61 are within the area enclosed by the mounting frame 1 when the full-view cabin door is open, so that neither the handle nor the cam 61 affects the rotation of the cabin door. Since the range of motion of the handle overlaps with the range of the transparent viewing window 22, a support block is provided between the handle on the outside of the cabin door and the outer frame 2 of the cabin door. A connecting column passes through the support block and the outer frame of the cabin door to connect the inner and outer handles and the cam 61, so that there is a sufficient distance between the handle and the outer frame 2 of the cabin door, so that the rotation of the handle does not interfere with the protruding transparent viewing window 22. Preferably, anti-slip textures or arc-shaped protrusions can also be provided on the handle to facilitate the application of force by the personnel to grip the handle. The cam 61 rotates from its extreme position within the groove 64 to the point where it is completely within the groove 64. The rotation angle of the cam 61 is 90-120°, and the specific angle can be set according to operational needs. A limiting structure is provided on the outer frame 2 of the hatch to restrict the rotation angle of the cam 61 or the handle 62. In this embodiment, the side of the mating block 63 facing the sliding frame 3 is flush with the inner side of the mounting frame 1 facing away from the sliding frame 3. That is, the far end of the cam 61 enters the side range of the mounting frame 1 at the same time as it enters the groove 64.

[0040] In one embodiment, a flange is provided on the inner side of the hatch outer frame. The flange is located between the first abutting edge 11 at the top and bottom of the mounting frame 1, and the flange abuts against the opposite sides of the upper and lower first abutting edges 11 to limit the up and down swaying of the hatch. In this embodiment, the limiting rod 21 is provided on the side of the flange facing the interior of the fuselage.

[0041] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An installation structure for a helicopter full-view cabin door, characterized in that, The system includes a mounting frame (1) on the fuselage, a door outer frame (2) and a sliding frame (3). The mounting frame (1) is used to mount the door outer frame (2). The sliding frame (3) is slidably mounted on the inner side wall of the cockpit. The sliding frame (3) slides along the front-rear direction of the helicopter and is located on either the nose or tail of the helicopter corresponding to the mounting frame (1). A connecting frame (5) is fixed on one side of the door outer frame (2). One side of the connecting frame (5) extends into the fuselage and is hinged to the sliding frame (3). A limiting plate (51) is provided on the connecting frame (5) to abut against the inner side of the mounting frame (1). A door lock (6) is provided on the other side of the door outer frame (2). The door lock (6) and the other side of the mounting frame (1) corresponding to the nose or tail of the helicopter cooperate to limit the closed state of the door. The upper and lower sides of the mounting frame (1) are provided with first abutting edges (11) that abut against the upper and lower sides of the hatch outer frame (2). The inner sides of the top and bottom of the hatch outer frame (2) are provided with limiting rods (21). The limiting rods (21) and the portion of the hatch outer frame (2) that abut against the first abutting edge (11) are spaced apart. The first abutting edge (11) is provided with a through groove (13) through which the limiting rod (21) passes. When the full-view hatch is in the open state, the hinge point of the sliding frame (3) and the connecting frame (5) is located in the area enclosed by the mounting frame (1); rotate the full-view hatch until the hatch outer frame (2) abuts against the first abutting edge (11) and the limiting rod (21) passes through the through groove (13), push the hatch outer frame (2) to move the hinge point of the sliding frame (3) and the connecting frame (5) to the outside of the area enclosed by the mounting frame (1), so that the full-view hatch is in the closed state, the limiting plate (51) abuts against the inner wall of the mounting frame (1), the limiting rod (21) and the inner side of the first abutting edge (11) abut against each other, and the inner sides of the top and bottom of the hatch outer frame (2) abut against the outer side of the first abutting edge (11).

2. The installation structure of the helicopter full-view cabin door according to claim 1, characterized in that, The inner side wall of the cockpit is provided with a slide rail (4), and a slider (41) is provided on the slide rail (4). The slide frame (3) and the slider (41) are detachably connected.

3. The installation structure of the helicopter full-view cabin door according to claim 2, characterized in that, The slide rail (4) has a fixed plate (42) at one end away from the hinge point of the sliding frame (3). The slider (41) has a slide rod (43) on the side facing the fixed plate (42). The fixed plate (42) has a hole for the slide rod (43) to pass through. A spring (44) is sleeved on the outer periphery of the slide rod (43) between the fixed plate (42) and the slider (41). When the full-view hatch is closed, the spring (44) is in a compressed state.

4. The installation structure of the helicopter full-view cabin door according to any one of claims 1 to 3, characterized in that, The door lock (6) includes a rotatable cam (61) and a handle (62) mounted on the outer frame (2) of the hatch. The axial direction of the cam (61) is along the wall thickness direction of the full-view hatch. The handle (62) and the cam (61) are fixedly connected. The handle (62) drives the cam (61) to rotate. A mating block (63) is provided on the inner side wall of the mounting frame (1) that matches the door lock (6). The mating block (63) is provided with a groove (64) for the distal end of the cam (61) to extend into. The groove (64) passes through the axis of the cam (61). And the straight line parallel to the sliding direction of the sliding frame (3) is the first straight line. When the full-view hatch is in the closed state, the angle between the line connecting the farthest point of the cam (61) and the axis of the cam (61) and the first straight line is 5-20°. The far end of the cam (61) abuts against the bottom of the groove (64) and abuts against the top or bottom wall of the groove (64). During the process of the far end of the cam (61) rotating from the opening of the groove (64) to the limit position inside the groove (64), the far end of the cam (61) passes through the first straight line.

5. The installation structure of the helicopter full-view cabin door according to claim 4, characterized in that, The mounting frame (1) has a second abutment edge (12) on the side away from the sliding frame (3). When the full-view hatch is in the closed state, the side of the hatch outer frame (2) with the door lock (6) abuts against the second abutment edge (12).

6. The installation structure for the helicopter full-view cabin door according to claim 5, characterized in that, The mounting frame (1) is coated with a self-lubricating coating on the side surface of the first abutting edge (11) and the second abutting edge (12) and the inner surface of the mounting frame (1) corresponding to the limiting plate (51). The area of ​​the hatch outer frame (2) that abuts the first abutting edge (11) and the second abutting edge (12) and the side of the limiting plate (51) facing the mounting frame (1) are provided with sealing strips, and the inner edge of the side of the mounting frame (1) corresponding to the limiting plate (51) is rounded.

7. The installation structure for the helicopter full-view cabin door according to claim 4, characterized in that, The sliding frame (3) is located on the side of the mounting frame (1) corresponding to the nose of the helicopter. The door lock (6) is located on the side of the cabin door outer frame (2) corresponding to the tail. The handle (62) includes a connecting post and a grip. The connecting post is connected to the cam (61). One end of the grip is connected to the connecting post. The other end of the grip is a free end. When the grip is rotated so that the free end moves closer to the nose, the far end of the cam (61) rotates from the range of the full-view cabin door into the groove (64). When the grip is rotated so that the free end moves closer to the tail, the far end of the cam (61) rotates out of the groove (64).

8. The installation structure of the helicopter full-view cabin door according to claim 7, characterized in that, The grip is provided with anti-slip texture or arc-shaped raised structure.

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