Mounting structure for a helicopter all-round vision hatch

Abstract

The application provides a mounting structure of a helicopter all-view cabin door, and belongs to the technical field of helicopters. The mounting structure specifically comprises a mounting frame on a fuselage, a cabin door outer frame and a sliding frame. The sliding frame is slidably mounted on the inner side wall of the cockpit. The cabin door outer frame is fixed with a connecting frame. The connecting frame is hingedly connected with the sliding frame. The connecting frame is provided with a limiting plate abutting against the inner side of the mounting frame. The other side of the cabin door outer frame is provided with a door lock. The all-view cabin door is rotated to abut against a first abutting edge of the cabin door outer frame, and a limiting rod passes through a through slot. The cabin door outer frame is pushed to move the hinging point of the sliding frame and the connecting frame to the outside of the area surrounded by the mounting frame, so that the all-view cabin door is in a closed state. The limiting plate abuts against the inner side wall of the mounting frame, the inner side of the limiting rod and the first abutting edge abut against each other, and the inner side of the top and bottom of the cabin door outer frame abuts against the outer side of the first abutting edge. Through the processing scheme, the stability of the all-view cabin door in the closed state is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of helicopters, in particular to a mounting structure of a helicopter all-view cabin door. BACKGROUND

[0002] In the field of helicopter design, the field of view performance of the cockpit and the task cabin directly affects the flight safety and operation efficiency, especially in special operation scenarios such as search and rescue, reconnaissance, and power inspection, the demand for all-directional field of view of the operator is increasingly urgent. In order to meet this demand, the all-view cabin door emerges as the times require, which effectively reduces the blind area of the field of view and significantly improves the observation range of the personnel in the cabin to the environment around the fuselage by adopting a large-area outwardly convex arc-shaped or curved transparent view window structure.

[0003] However, the special structure of the all-view cabin door also brings challenges to its installation and stability performance. The existing all-view cabin door mostly adopts a traditional hinge type: the hinge type structure can realize the rotation opening of the cabin door, but in the closed state, it is only fixed by a single hinge shaft and a door lock. Due to the outward convexity of the transparent view window, the overall center of gravity of the cabin door is moved outward, and when the helicopter is impacted by airflow during flight, the outwardly convex cabin door is prone to shaking along the direction of the hinge shaft, and long-term use may cause problems such as structural fatigue;

[0004] Therefore, how to optimize the mounting structure of the cabin door while ensuring the all-view function, improve the stability in the closed state, and reduce the shaking problem caused by airflow impact has become a technical difficulty to be solved in the design of the all-view helicopter cabin door. SUMMARY

[0005] Therefore, the present application provides a mounting structure of a helicopter all-view cabin door, which solves the problem that the existing all-view cabin door is prone to shaking under the impact of airflow, and improves the stability of the all-view cabin door in the closed state.

[0006] The mounting structure of the helicopter all-view cabin door provided by the present application adopts the following technical solution:

[0007] A mounting structure of a helicopter all-view cabin door, comprising a mounting frame on a fuselage, a cabin door outer frame and a sliding frame, the mounting frame is used for mounting the cabin door outer frame, the sliding frame is slidably mounted on the inner side wall of the cockpit, the sliding frame slides along the front-rear direction of the helicopter, and the sliding frame is located on any one side of the mounting frame corresponding to the nose and tail of the helicopter, one side of the cabin door outer frame is fixed with a connecting frame, one side of the connecting frame extends into the interior of the fuselage and is hinged with the sliding frame, the connecting frame is provided with a limiting plate abutting against the inner side surface of the mounting frame, and the other side of the cabin door outer frame is provided with a door lock, the door lock and the other side of the mounting frame corresponding to the nose and tail of the helicopter cooperate to define the closed state of the cabin door;

[0008] The upper and lower sides of the mounting frame are provided with first abutting edges abutting the upper and lower sides of the cabin door outer frame, the inner sides of the top and bottom of the cabin door outer frame are provided with limiting rods, the limiting rods and the part of the cabin door outer frame abutting the first abutting edges are spaced apart, and the first abutting edges are provided with through grooves through which the limiting rods pass.

[0009] When the full-view cabin door is in the open state, the hinge point of the sliding frame and the connecting frame is located in the area surrounded by the mounting frame; the full-view cabin door is turned to abut the first abutting edge of the cabin door outer frame and the limiting rod passes through the through groove, the cabin door outer frame is pushed to move the hinge point of the sliding frame and the connecting frame to the outside of the area surrounded by the mounting frame, and the full-view cabin door is in the closed state, the limiting plate abuts the inner side wall of the mounting frame, the inner side of the limiting rod abuts the first abutting edge, and the inner sides of the top and bottom of the cabin door outer frame abut the outer side of the first abutting edge.

[0010] Optionally, the inner side wall of the cockpit is provided with a sliding rail, the sliding rail is provided with a sliding block, and the sliding frame and the sliding block are detachably connected.

[0011] Optionally, one end of the sliding rail away from the hinge point of the sliding frame is provided with a fixed plate, one side of the sliding block facing the fixed plate is provided with a sliding rod, the fixed plate is provided with a hole through which the sliding rod passes, a spring is sleeved on the outer periphery of the sliding rod between the fixed plate and the sliding block, and the spring is in a compressed state when the full-view cabin door is in the closed state.

[0012] Optionally, the door lock comprises a rotating cam mounted on the cabin door outer frame and a handle, the rotation axis of the cam is arranged in the thickness direction of the full-view cabin door, the handle is fixedly connected with the cam, the handle drives the rotation of the cam, the inner wall of the side of the mounting frame matched with the door lock is provided with a matching block, the matching block is provided with a groove into which the distal end of the cam extends, a straight line passing through the axis of the cam and parallel to the sliding direction of the sliding frame is a first straight line, when the full-view cabin door is in the closed state, the included angle between the distal end point of the cam and the axis of the cam and the first straight line is -0°, and the distal end of the cam abuts the bottom wall of the groove while abutting the top wall or the bottom wall of the groove, and the distal end of the cam passes through the first straight line in the process of rotating from the slot opening of the groove into the groove to the limit position.

[0013] Optionally, the mounting frame is provided with a second abutting edge on the side away from the sliding frame, and the side of the cabin door outer frame provided with the door lock abuts on the second abutting edge when the full-view cabin door is in the closed state.

[0014] Optionally, the installation frame is coated with a self-lubricating coating on the side surface corresponding to the first and second abutting edges and the inner side surface of the installation frame corresponding to the limiting plate, the area of the door outer frame abutting the first and second abutting edges and the limiting plate towards the side of the installation frame are provided with sealing rubber strips, and the side inner corner of the installation frame corresponding to the limiting plate is rounded.

[0015] Optionally, the sliding frame is located on the side of the installation frame corresponding to the nose of the helicopter, the door lock is located on the side of the door outer frame corresponding to the tail of the helicopter, the handle includes a connecting column and a grip, the connecting column is connected with the cam, one end of the grip is connected with the connecting column, the other end of the grip is a free end, when the free end of the grip is turned towards the nose of the helicopter, the distal end of the cam is turned into the groove from the range of the full-view door, and when the free end of the grip is turned towards the tail of the helicopter, the distal end of the cam is turned out of the groove.

[0016] Optionally, the grip is provided with anti-skid lines or arc-shaped protruding structures.

[0017] In summary, the present application has the following beneficial technical effects:

[0018] When the full-view door is in the closed state, the limiting plate abuts against the inner side wall of the installation frame, the inner side of the limiting rod and the first abutting edge, and the inner side of the top and bottom of the door outer frame abuts against the outer side of the first abutting edge. In the present application, through the abutment of the limiting plate and the installation frame and the bilateral abutment of the abutting piece on the door outer frame and the installation frame, the stability of the full-view door in the closed state is improved, and the problem of large internal and external shaking of the full-view door caused by the influence of airflow during the flight of the helicopter due to the structural characteristics of the outward protruding full-view door is solved. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0020] Figure 1 Fig. 1 is a schematic diagram of the outside structure of the full-view door of the helicopter;

[0021] Figure 2 Fig. 2 is a schematic diagram of the installation structure when the full-view door of the helicopter is closed and locked;

[0022] Figure 3 Fig. 3 is a schematic diagram of the installation structure when the full-view door of the helicopter is closed and locked.

[0023] Figure 4 This is a schematic diagram of the installation structure when the helicopter's all-view cabin door is open, as per this application.

[0024] 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;

[0025] Figure 6 This is a schematic diagram of the installation structure when the helicopter's full-view cabin door is half-open.

[0026] 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

[0027] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0028] 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.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] This application provides an installation structure for a helicopter full-view cabin door.

[0033] 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.

[0034] 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.

[0035] like Figure 2 and Figure 3As shown, the upper and lower sides of the mounting frame 1 are provided with first abutting edges 11 abutting the upper and lower sides of the cabin door outer frame 2, the inner sides of the top and bottom of the cabin door outer frame 2 are provided with limiting rods 21 fixed on the cabin door outer frame 2, the limiting rods 21 and the part of the cabin door outer frame 2 abutting the first abutting edges 11 are spaced apart, and the first abutting edges 11 are provided with through grooves 13 for the limiting rods 21 to pass through.

[0036] As shown in Figure 2 , Figure 3 and Figure 4 , when the full-view cabin door is in the open state, the hinge points of the sliding frame 3 and the connecting frame 5 are located in the area enclosed by the mounting frame 1, at this time the cabin door outer frame 2 can rotate around the sliding frame 3 to realize free rotation of the full-view cabin door; the full-view cabin door is rotated to the position where the cabin door outer frame 2 abuts against the first abutting edges 11 and the limiting rods 21 pass through the through grooves 13, the sliding frame 3 and the connecting frame 5 are pushed to move the hinge points 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 cabin door is in the closed state, at this time, the limiting plate 51 abuts against the inner side wall of the mounting frame 1, the inner sides of the limiting rods 21 and the first abutting edges 11 abut against each other, and the inner sides of the top and bottom of the cabin door outer frame 2 abut against the outer sides of the first abutting edges 11. In this application, through the abutment of the limiting plate 51 and the mounting frame 1 and the bilateral abutment of the cabin door outer frame 2 and the abutting edges on the mounting frame 1, the stability of the full-view cabin door in the closed state is improved, and the problem of large internal and external shaking of the full-view cabin door caused by the influence of air flow during the flight of the helicopter due to the structural characteristics of the outward protruding full-view cabin door is solved.

[0037] In one embodiment, the limiting rods 21 are cylindrical, and the arc-shaped outer circumferential surface of the limiting rods is used to abut against the inner side of the mounting frame 1, so that the limiting rods 21 can form overlapping abutment with the first abutting edges 11 when the cabin door slides.

[0038] The inner side wall of the cockpit is provided with a sliding rail 4, the sliding rail 4 is provided with a sliding block 41, and the sliding frame 3 and the sliding block 41 are detachably connected. In the embodiment of the application, two spaced-apart sliding rails 4 are provided on the inner wall of the fuselage of the helicopter cockpit, the sliding rails 4 are located on the side wall of the fuselage between the mounting frame 1 and the nose, the sliding frame 3 includes two horizontal rods 31 corresponding to the two sliding rails 4, and the two horizontal rods 31 can be connected by a vertical rod to improve the stability and synchronism of the sliding of the sliding frame 3. Among them, the sliding rail 4 and the sliding block 41 are directly purchased as a complete set of products, generally the two ends of the sliding rail 4 are provided with limiting mechanisms for limiting the sliding block 41 from sliding off, and the specific structure is purchased according to the demand, which will not be described here.

[0039] In the embodiment of the present application, when the full-view cabin door is in the closed state, the side of the one side of the connecting frame 5 installed on the outer frame 2 abuts against the side of the one side of the corresponding sliding frame 3 of the installation frame 1.

[0040] As shown in Figure 2 , Figure 3 and Figure 5 , the connecting frame 5 and the sliding frame 3 are more specifically structured as follows:

[0041] In one embodiment, the connecting frame 5 comprises an installation plate and a hinged seat 53 at the upper and lower ends of the installation plate, the height of the installation plate is within the range enclosed by the installation frame 1, the hinged seat 53 of the installation plate is hinged with the crossbar 31, the hinged shaft is arranged along the height direction of the fuselage, the installation plate comprises a connecting plate 52 connected with the outer frame 2 of the cabin door and the limiting plate 51, and in order to avoid the rotation of the crossbar 31 interfering with the outer frame 2 of the cabin door and the connecting frame 5, the crossbar 31 comprises a main body section 33 and a hinged section, the main body section 33 is fixedly connected by bolts and sliding blocks, the hinged 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 with the main body section 33, the other end of the U-shaped frame 32 is hinged with the hinged seat 53, and the internal region of the U-shaped frame 32 provides sufficient space for the rotation of the outer frame 2 of the cabin door and the connecting frame 5, and the hinged seat 53 extends outwardly from the installation plate in a direction perpendicular to the installation plate.

[0042] The fixed plate 42 is arranged at the end of the sliding rail 4 away from the hinged point of the sliding frame 3, the sliding block 41 is provided with a sliding rod 43 on the side facing the fixed plate 42, the fixed plate 42 is provided with a hole through which the sliding rod 43 passes, the sliding rod 43 between the fixed plate 42 and the sliding block 41 is sleeved with a spring 44, the two ends of the spring 44 only contact the fixed plate 42 and the sliding block 41, and there is no substantial connecting structure between the spring 44 and the fixed plate 42 and between the spring 44 and the sliding block 41, so that the action force of the stretched spring 44 needs to be overcome when the door is opened, the spring 44 is in a compressed state when the full-view cabin door is in the closed state, and whether the spring 44 is in the compressed state when the full-view cabin door needs to be rotated is not limited by the present application. However, as an embodiment, when the cabin door 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 sliding block 41 and the fixed plate 42 at this time, that is, in this embodiment, the spring 44 only provides assistance to the sliding of the cabin door in the initial stage of opening the cabin door, and does not provide assistance in the entire sliding stage. The design can avoid the cabin door being resisted by the spring 44 in the early stage of sliding the cabin door in the process of closing the cabin door, and only needs to overcome the elastic force of the spring 44 in the later stage to compress the spring 44. The length of the sliding rod 43 needs to be arranged to be still arranged in the fixed plate 42 when sliding to the limit position.

[0043] In one embodiment, a protective shell is arranged on the inner wall of the cockpit and covers the outer periphery of the slide rail 4, the slide block 41 and the slide frame 3. A passage is arranged on the side wall of the protective shell and penetrates the slide frame 3.

[0044] As shown in Figure 2 , Figure 5 and Figure 6 , in one embodiment, the first abutting edge 11 is provided with a clearance gap 14 near one side of the slide frame 3. The upper and lower top ends of the door outer frame 2 pass through the clearance gap 14 during the rotation to the open position. The design of the clearance gap 14 avoids the interference of the first abutting edge 11 on the installation frame 1 to the rotation of the door outer frame.

[0045] As shown in Figure 1 , Figure 2 and Figure 3As shown, the door lock 6 comprises a rotating cam 61 mounted on the cabin door outer frame 2 and a handle 62, the handle 62 is arranged on the inner and outer sides of the cabin door outer frame 2, the rotation axis of the cam 61 is arranged along the thickness direction of the wall of the full-view cabin door, the handle 62 is fixedly connected with the cam 61, the handle 62 drives the rotation of the cam 61, a matching block 63 is arranged on the inner wall of the side of the mounting frame 1 matched with the door lock 6, the matching block 63 is provided with a groove 64 for the distal end of the cam 61 to extend into, a straight line passing through the axis of the cam 61 and parallel to the sliding direction of the sliding frame 3 is a first straight line, when the full-view cabin door is in the closed state, the included angle between the distal end point of the cam 61 and the axis of the cam 61 and the first straight line is 5-20°, and the distal end of the cam 61 abuts against the top wall or the bottom wall of the groove 64 while abutting against the groove bottom of the groove 64, in the process of rotating the distal end of the cam 61 from the groove opening of the groove 64 into the groove 64 to the limit position, the distal end of the cam 61 passes through the first straight line. When the full-view cabin door is in the closed state, the cam 61 is arranged to be inclined relative to the sliding direction of the cabin door, and the cam 61 has a tendency to continue to rotate under the action of the spring 44, but the distal end of the cam 61 is limited by the inner wall of the groove 64, thereby stabilizing the position of the cam 61, and realizing the function of locking the handle 62 state when the full-view cabin door is in the closed state. In an embodiment, the cam 61 is located outside the groove 64, at this time the full-view cabin door can be rotated, the distal end of the cam 61 faces downward, when the full-view cabin door contacts the first abutting edge 11 of the mounting frame 1, rotating the handle 62 drives the rotation of the cam 61, the distal end of the cam 61 enters the groove 64 while rotating upward, after passing through the first straight line, the distal end of the cam 61 abuts against the top wall of the groove 64 in an inclined state, in this process, as the cam 61 rotates, the inner wall of the groove 64 abutting against the cam 61 gradually pushes the cabin door outer frame 2 to one side of the sliding frame 3 to compress the spring 44 until the cabin door outer frame 2 reaches the limit position, at this time, the distal end of the cam 61 is located above the first straight line, under the action of the spring 44, the cabin door outer frame 2 has a tendency to move to one side of the door lock 6, so that the distal end of the cam 61 has a tendency to continue to move upward, but the cam 61 cannot continue to rotate under the limiting line of the top wall of the groove 64, and the distal end of the cam 61 will not fall downward in the natural state to cause the door lock 6 to fail.

[0046] In an embodiment, a protective cover is arranged on the outer periphery of the cam 61 on the inner side of the cabin door outer frame 2, and the protective cover is provided with a passage for the rotation of the cam 61.

[0047] As Figure 1 and Figure 2As shown, the mounting frame 1 is provided with a second abutting edge 12 on the side away from the sliding frame 3, and the side of the door outer frame 2 provided with the door lock 6 abuts against the second abutting edge 12 when the all-view door is in the closed state. The width of the second abutting edge 12 covers the sliding range of the door outer frame 2 away from the sliding frame 3 during locking of the door, thereby ensuring the sealing when the door is closed.

[0048] The side surface of the mounting frame 1 corresponding to the first abutting edge 11 and the second abutting edge 12 and the inner side surface of the mounting frame 1 corresponding to the limiting plate 51 are coated with a self-lubricating coating, and the area of the door outer frame 2 abutting against 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 rubber strips. In the embodiment of the application, the self-lubricating coating is Teflon. While ensuring sealing, the self-lubricating coating avoids abrasion and damage to the sealing rubber strips. The side inner side edge of the limiting plate 51 corresponding to the mounting frame 1 is rounded, and the limiting plate 51 is guided when it starts to contact the mounting frame 1 when the door is closed, thereby ensuring smooth closing of the door.

[0049] 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 door outer frame 2 corresponding to the tail of the helicopter. The handle 62 includes a connecting column and a grip. The connecting column is connected with the cam 61, and one end of the grip is connected with the connecting column. The other end of the grip is a free end. When the grip is rotated to make the free end approach the nose, the distal end of the cam 61 rotates from the range of the all-view door into the recess 64. When the grip is rotated to make the free end approach the tail, the distal end of the cam 61 rotates out of the recess 64. The force of the personnel on the handle 62 and the sliding direction of the all-view door are consistent when the door lock 6 is opened and closed.

[0050] In the embodiment of the present application, when the full-view cabin door is in the closed state, the free end of the handle faces the nose direction, the distal end of the cam 61 faces the tail direction and is located in the groove 64; when the full-view cabin door is in the open state, the free end of the handle faces the upper side of the aircraft, the distal end of the cam 61 faces the lower side of the aircraft, so that the handle and the cam 61 are both located in the area surrounded by the mounting frame 1 when the full-view cabin door is opened, and neither the handle nor the cam 61 affects the rotation of the cabin door. Since the range of movement of the handle coincides with the range of the transparent viewing window 22, a support block is arranged between the handle outside the cabin door and the cabin door outer frame 2, and the connecting column passes through the support block and the cabin door outer frame to connect the inner and outer handles and the cam 61, so as to keep a sufficient distance between the handle and the cabin door outer frame 2, so that the rotation of the handle does not interfere with the outwardly convex transparent viewing window 22. Preferably, anti-slip patterns or arc-shaped protruding structures can be arranged on the handle to facilitate personnel to exert force on the handle. The cam 61 rotates from the limit position where the distal end is located in the groove 64 to the position where the cam 61 is completely located in the range of the groove 64, and the angle of rotation of the cam 61 is 90-120°. The specific angle can be set according to the operation needs, and a limiting structure for limiting the rotation angle of the cam 61 or the handle 62 is arranged on the cabin door outer frame 2. In the embodiment of the present application, the mating block 63 faces the side of the sliding frame 3 and the inner side of the mounting frame 1 facing away from the sliding frame 3 is flush, that is, the distal end of the cam 61 starts to enter the range of the side of the mounting frame 1 at the same time as it enters the groove 64.

[0051] In one embodiment, a flange is arranged on the inner side of the cabin door outer frame, the flange is located between the first abutting edges 11 at the top and the bottom of the mounting frame 1, and the flange abuts the side edges opposite to the upper and lower first abutting edges 11, thereby limiting the up-and-down movement of the cabin door. In this embodiment, the limiting rod 21 is arranged on the side of the flange facing the interior of the fuselage.

[0052] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto. Any changes or replacements within the technical range disclosed in the present application can be easily thought of by those skilled in the art, and should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection 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); 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 sliding frame (3) and the slider (41) are detachably connected. 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.

2. The installation structure of the helicopter full-view cabin door according to claim 1, 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.

3. The installation structure of the helicopter full-view cabin door according to claim 2, 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).

4. The installation structure of the helicopter full-view cabin door according to claim 3, 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.

5. The installation structure of the helicopter full-view cabin door according to claim 2, 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).

6. The installation structure for the helicopter full-view cabin door according to claim 5, characterized in that, The grip is provided with anti-slip texture or arc-shaped raised structure.

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