Helicopter airborne operation guarantee subsystem stretcher buffering and fixing structure

Abstract

The invention provides a stretcher buffering and fixing structure of a helicopter airborne operation guarantee subsystem, and relates to the technical field of emergency rescue stretcher fixing. The stretcher buffering and fixing structure of the helicopter airborne operation guarantee subsystem is arranged at the position, used for bearing a stretcher, of an airborne fixing frame, four locking devices are evenly arranged on the upper end face of an upper-layer fixing frame and the upper end face of the airborne fixing frame, and the locking devices generate downward displacement after the stretcher is placed on the locking devices. The stretcher is limited from the upper part of the stretcher main beam, so that the stretcher forms an automatic locking action in the placing process; an unlocking device is arranged among the four locking devices, the unlocking device has a locking effect on the displacement of the locking devices when no external force is applied to the stretcher and the stretcher is placed on the locking devices, and the unlocking device applies pressure through the external force to unlock the displacement locking of the locking devices.

Description

Technical Field

[0001] This application relates to the field of emergency rescue stretcher fixation technology, and more specifically, to a stretcher buffer fixation structure for a helicopter airborne operation support subsystem. Background Technology

[0002] In the field of emergency rescue, helicopters occupy a central position due to their rapid response and high mobility. However, the stable fixation and rapid loading and unloading of stretchers within the helicopter cabin during rescue operations remains a critical challenge for the industry. To further improve rescue efficiency and minimize the risk of secondary injury to patients during helicopter flight and transport, there is an urgent need to develop a stretcher cushioning and fixation structure adapted to the helicopter's onboard environment. This would ensure the stability of the stretcher within the cabin while simultaneously enabling rapid loading and unloading. Summary of the Invention

[0003] This application aims to at least solve one of the technical problems existing in the prior art. To this end, this application proposes a stretcher buffer and fixing structure for a helicopter airborne operation support subsystem. The structure is installed on an airborne mounting frame at the position for supporting the stretcher. A vertical frame is fixedly connected to one side of the airborne mounting frame, and an upper mounting frame is fixedly connected to the vertical frame. The upper surfaces of both the upper mounting frame and the airborne mounting frame are used to support the stretcher. Four locking devices are evenly arranged on the upper surfaces of both the upper mounting frame and the airborne mounting frame. The positions of the four locking devices correspond to the four support points of the stretcher. The four locking devices are identical in size. The locking devices are used when the stretcher is placed on... Afterwards, a downward displacement occurs, limiting the stretcher from above the main beam, thus automatically locking the stretcher during placement. An unlocking device is provided between the four locking devices. When the stretcher is placed on the locking device without external force, the unlocking device locks the displacement of the locking device, preventing it from resetting. The unlocking device releases its own displacement lock on the locking device by applying external pressure, thereby releasing the locking device from locking the main beam of the stretcher, allowing the stretcher to be removed from the locking device.

[0004] Preferably, the locking device includes a buffer assembly fixed to the upper surface of the airborne mounting frame and the upper mounting frame, a guide assembly fixed to the buffer assembly, a positioning assembly slidably connected to the guide assembly, and the positioning assembly and the buffer assembly being connected.

[0005] Preferably, the buffer assembly includes a positioning cylinder, a positioning shaft, and a damping spring. The positioning cylinder is fixedly connected to the upper end face of the airborne mounting frame and the upper mounting frame; the positioning shaft is coaxially fixedly connected to the bottom of the positioning cylinder; and the damping spring is sleeved on the positioning shaft.

[0006] Preferably, the guide assembly includes an L-shaped fixing plate fixed to the top of the positioning cylinder, an inclined plate fixed to one end of the L-shaped fixing plate, a hollow groove provided on the upper side of the inclined surface of the inclined plate, a first sliding groove and a second sliding groove arranged side by side on both sides of the hollow groove, and a positioning groove provided through the end of the L-shaped fixing plate fixed to the inclined plate.

[0007] Preferably, the positioning component includes a V-shaped plate disposed on the upper side of the L-shaped fixing plate. The upper side of the V-shaped plate is provided with a V-shaped bearing end, which is used to support the main beam of the stretcher. A sliding shaft is fixedly connected to the bottom end of the bearing end. The sliding shaft slides through the L-shaped fixing plate and is slidably inserted into the positioning cylinder. A guide cavity is coaxially disposed inside the sliding shaft. The guide cavity and the positioning shaft are slidably connected. A connecting rod is hinged to one end of the V-shaped plate near the inclined plate. An abutment plate is hinged to the other end of the connecting rod. The abutment plate is horizontally disposed and slidably disposed in the positioning groove. Two first sliding pins and a second sliding pin are symmetrically fixed to both sides of the abutment plate. The first sliding pins and the second sliding pins slide in the first sliding groove and the second sliding groove, respectively. The first sliding pins and the connecting rod are rotatably connected.

[0008] Preferably, the two L-shaped fixing plates, the two inclined plates, and the two abutment plates are symmetrically arranged at the same end of the airborne fixing frame, with the tops of the two inclined plates far apart from each other and the inner parts of the two abutment plates close to each other.

[0009] Preferably, the unlocking device includes two reset components, a pressing plate, and two connecting components. The two reset components are arranged along the length of the airborne mounting frame. The pressing plate is slidably disposed within the two reset components. The two connecting components are symmetrically disposed on both sides of the pressing plate and are slidably inserted into the four positioning slots.

[0010] Preferably, the reset assembly includes a positioning frame fixed to the upper surface of the airborne mounting frame and the upper mounting frame, guide rods are fixed to the top and bottom ends of the positioning frame, a reset spring is sleeved on the guide rod, and the pressing plate is slidably sleeved on the guide rod and pressed against the top end of the reset spring.

[0011] Preferably, a pressing block is provided at the center of the bottom side of the pressing plate, and first inclined surfaces are symmetrically provided on both sides of the pressing block.

[0012] Preferably, the connecting assembly includes a first support rod disposed on one side of the bottom of the pressing plate, a second support rod fixedly connected to the side of the first support rod away from the pressing plate, two L-shaped rods symmetrically fixed to both ends of the second support rod, a second inclined surface that fits with the first inclined surface on the side of the first support rod facing the pressing block, a fixing block slidably sleeved on the first support rod, the fixing block being fixedly connected to the upper end face of the airborne fixing frame and the upper fixing frame, a sliding block fixedly sleeved on the first support rod, a sliding rod fixedly connected to one side of the sliding block, the sliding rod being slidably inserted into the fixing block, and a compression spring abutting against the fixing block being sleeved on the sliding rod.

[0013] The beneficial effects of a stretcher buffer and fixing structure for a helicopter airborne operation support subsystem according to an embodiment of this application are: 1. By applying pressure to four locking devices on the stretcher, the stretcher is automatically and quickly locked, and its position on the helicopter is determined; 2. By deforming the unlocking device under pressure and without pressure, the two actions of unlocking and locking the locking device are realized. Under pressure, the four locking devices can be quickly unlocked, and under no pressure, the four locking devices can be quickly locked. 3. By using the unlocking device, the stretcher can be locked and unlocked on the helicopter, improving rescue efficiency and ensuring the stability of the stretcher inside the helicopter cabin. 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. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram showing the position of a stretcher buffer fixing structure of a helicopter airborne operation support subsystem according to an embodiment of this application; Figure 2 This is a side view of a stretcher buffer fixing structure of a helicopter airborne operation support subsystem according to an embodiment of this application; Figure 3 This is an exploded view of the structure of a stretcher buffer fixing structure of a helicopter airborne operation support subsystem according to an embodiment of this application; Figure 4 This is a partial exploded view of the locking device according to an embodiment of this application; Figure 5 According to the embodiments of this application Figure 3 Enlarged view of A in the middle; Figure 6 According to the embodiments of this application Figure 3 Enlarged view of B in the middle; Figure 7 According to the embodiments of this application Figure 3 A magnified view of C.

[0016] Icons: 1. Airborne mounting frame; 11. Stand; 12. Upper mounting frame; 2. Locking device; 21. Buffer assembly; 211. Positioning cylinder; 212. Positioning shaft; 213. Damping spring; 22. Guide assembly; 221. L-shaped fixing plate; 222. Inclined plate; 223. Hollow groove; 224. First slide groove; 225. Second slide groove; 226. Positioning groove; 23. Positioning assembly; 231. V-shaped plate; 232. Bearing end; 233. Sliding shaft; 234. Guide cavity; 235. 236. Connecting rod; 237. Abutment plate; 238. First sliding pin; 239. Second sliding pin; 30. Unlocking device; 31. Reset assembly; 311. Positioning frame; 312. Guide rod; 313. Reset spring; 32. Pressing plate; 321. Pressing block; 322. First inclined section; 33. Connecting assembly; 331. First support rod; 332. Second support rod; 333. L-shaped rod; 334. Second inclined section; 335. Fixing block; 336. Sliding block; 337. Slide rod; 338. Compression spring. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, not all of them. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0018] The following describes in detail, through specific embodiments, a stretcher buffer and fixing structure of a helicopter airborne operation support subsystem of the present invention, which is set at the position of the airborne fixing frame 1 for supporting the stretcher.

[0019] like Figures 1-7As shown, an upright frame 11 is fixed to one side of the airborne mounting frame 1, and an upper mounting frame 12 is fixed to the upright frame 11. The upper end surfaces of both the upper mounting frame 12 and the airborne mounting frame 1 are used to support the stretcher. Four locking devices 2 are evenly arranged on the upper end surfaces of the upper mounting frame 12 and the airborne mounting frame 1. The positions of the four locking devices 2 correspond to the four support points of the stretcher. The four locking devices 2 are exactly the same size. After the stretcher is placed on them, the locking devices 2 will move downward and limit the stretcher from above the main beam of the stretcher, so that the stretcher will automatically lock during placement. An unlocking device 3 is arranged between the four locking devices 2. When no external force is applied, the unlocking device 3 will lock the displacement of the locking device 2 after it is placed on the locking device 2, preventing the locking device 2 from resetting. When external force is applied, the unlocking device 3 will release itself from locking the displacement of the locking device 2, and then release the locking device 2 from locking the main beam of the stretcher, so that the stretcher can be removed from the locking device 2.

[0020] Specifically, the locking device 2 includes a buffer assembly 21 fixed to the upper surface of the airborne fixed frame 1 and the upper fixed frame 12. A guide assembly 22 is fixed to the buffer assembly 21. A positioning assembly 23 is slidably connected to the guide assembly 22. The positioning assembly 23 is connected to the buffer assembly 21.

[0021] The buffer assembly 21 includes a positioning cylinder 211, a positioning shaft 212, and a damping spring 213. The positioning cylinder 211 is fixed to the upper end face of the airborne fixed frame 1 and the upper fixed frame 12. The positioning shaft 212 is coaxially fixed to the bottom of the positioning cylinder 211. The damping spring 213 is sleeved on the positioning shaft 212.

[0022] It should be noted that the damping spring 213 in the specific embodiment of this application can be a damping spring shock absorber in the prior art, which plays a buffering role against vibrations during flight. The illustration is only a simplified representation.

[0023] Furthermore, the guide assembly 22 includes an L-shaped fixing plate 221 fixed to the top of the positioning cylinder 211. One end of the L-shaped fixing plate 221 is inclinedly fixed to an inclined plate 222. A hollow groove 223 is provided on the upper side of the inclined surface of the inclined plate 222. A first sliding groove 224 and a second sliding groove 225 are arranged side by side on both sides of the hollow groove 223. A positioning groove 226 is provided through the end of the L-shaped fixing plate 221 that is fixed to the inclined plate 222.

[0024] Specifically, the positioning component 23 includes a V-shaped plate 231 disposed on the upper side of the L-shaped fixing plate 221. A V-shaped bearing end 232 is disposed on the upper side of the V-shaped plate 231. The bearing end 232 is used to support the main beam of the stretcher. A sliding shaft 233 is fixedly connected to the bottom end of the bearing end 232. The sliding shaft 233 slides through the L-shaped fixing plate 221 and slides into the positioning cylinder 211. A guide cavity 234 is coaxially disposed inside the sliding shaft 233. The guide cavity 234 and the positioning shaft 212 are slidably connected. A connecting rod 235 is hinged to one end of the V-shaped plate 231 near the inclined plate 222. An abutment plate 236 is hinged to the other end of the connecting rod 235. The abutment plate 236 is horizontally set and slidably set in the positioning groove 226. Two first sliding pins 237 and second sliding pins 238 are symmetrically fixed to both sides of the abutment plate 236. The first sliding pins 237 and second sliding pins 238 slide in the first sliding groove 224 and the second sliding groove 225 respectively. The first sliding pins 237 and the connecting rod 235 are rotatably connected.

[0025] It should be noted that, as Figure 1 and Figure 2 As shown, two L-shaped fixing plates 221, two inclined plates 222 and two abutment plates 236 are symmetrically arranged at the same end of the airborne fixing frame 1, with the tops of the two inclined plates 222 being far apart from each other and the inner parts of the two abutment plates 236 being close to each other.

[0026] Understandably, this design will limit the stretcher's horizontal movement after it is placed on it, preventing it from shifting parallel to the bottom of the cabin.

[0027] In a specific embodiment of this application, the unlocking device 3 includes two reset components 31, a pressing plate 32, and two connecting components 33. The two reset components 31 are arranged along the length direction of the airborne fixing frame 1. The pressing plate 32 is slidably disposed in the two reset components 31. The two connecting components 33 are symmetrically arranged on both sides of the pressing plate 32 and are slidably inserted into the four positioning slots 226 respectively.

[0028] The reset assembly 31 includes a positioning frame 311 fixed to the upper end face of the airborne fixed frame 1 and the upper fixed frame 12. Guide rods 312 are fixed to the top and bottom ends of the positioning frame 311. A reset spring 313 is sleeved on the guide rods 312. The pressing plate 32 is slidably sleeved on the guide rods 312 and pressed against the top end of the reset spring 313.

[0029] Furthermore, a pressing block 321 is provided at the center of the bottom side of the pressing plate 32, and first inclined surfaces 322 are symmetrically provided on both sides of the pressing block 321.

[0030] Furthermore, the connecting assembly 33 includes a first support rod 331 disposed on one side of the bottom of the pressing plate 32, a second support rod 332 fixedly connected to the side of the first support rod 331 away from the pressing plate 32, two L-shaped rods 333 symmetrically fixed to both ends of the second support rod 332, a second inclined surface 334 that fits with the first inclined surface 322 disposed on the side of the first support rod 331 facing the pressing block 321, a fixing block 335 slidably sleeved on the first support rod 331, the fixing block 335 fixedly connected to the upper end face of the airborne fixing frame 1 and the upper fixing frame 12, a sliding block 336 fixedly sleeved on the first support rod 331, a sliding rod 337 fixedly connected to one side of the sliding block 336, the sliding rod 337 slidably inserted into the fixing block 335, and a compression spring 338 abutting against the fixing block 335 sleeved on the sliding rod 337.

[0031] It should be noted that the compression spring 338 is a tension spring.

[0032] In summary, it can be understood that in the specific embodiments of this application, during emergency rescue operations, after the rescue personnel lift the stretcher carrying the injured person into the helicopter cabin, they place the crossbeams on both sides of the stretcher onto two sets of V-shaped plates 231 arranged along the length of the airborne fixed frame 1 or the upper fixed frame 12. During placement, due to the open design of the V-shaped plates 231, the stretcher crossbeams can easily fall directly into the corresponding bearing ends 232. After being compressed, the V-shaped plates 231 will move downward along the positioning axis 212 via the sliding shaft 233 and compress the damping spring 213. It should be noted that the elastic force of the damping spring 213 is set to be greater than the sum of the weight of the stretcher and the injured person on it, i.e. Even after the damping spring 213 supports the stretcher, it will not be compressed to its limit. During the descent of the V-shaped plate 231 under pressure, the connecting rod 235 hinged to it will pull the first sliding pin 237 downward along the first sliding groove 224. A second sliding pin 238 is also fixed to the side wall of the abutment plate 236, and the second sliding pin 238 slides within the second sliding groove 225. The second sliding groove 225 and the first sliding groove 224 are parallel. Therefore, the abutment plate 236 will be pulled downward along the hollow groove 223. It should be noted that in the initial state (i.e., when the stretcher is pressed against the V-shaped plate 231), the end of the abutment plate 236 away from the first sliding pin 237 does not obstruct the stretcher beam from sliding downward. The displacement within the V-shaped plate 231 occurs when the stretcher beam presses down on the V-shaped plate 231 to its limit. At this point, the end of the abutment plate 236 away from the first sliding pin 237 moves to the top of the stretcher beam, thus restricting its movement. Furthermore, when placing the stretcher, rescuers must press down on the pressing plate 32 in advance or simultaneously to displace the pressing block 321 downwards. This, in turn, presses the first inclined surfaces 322 on both sides against the second inclined surfaces 334 of the first support rods 331 on both sides, causing the two first support rods 331 to move away from each other. This action causes the two sets of L-shaped rods 333 on both sides of the pressing plate 32 to move along the positioning groove 226 away from the end of the V-shaped plate 231. Directional displacement, that is, to make way for the downward displacement of the V-shaped plate 231, after the stretcher is placed, the pressing plate 32 is released. Under the reset action of the reset spring 313, the pressing plate 32 is reset. At this time, under the tension of the compression spring 338, the first support rod 331 will force the sliding block 336 to drive the first support rod 331 to reset, so that the second inclined part 334 still abuts against the first inclined part 322. At this time, the end of the L-shaped rod 333 inserted into the positioning groove 226 will move upward towards the end of the V-shaped plate 231 and press against the V-shaped plate 231, which restricts the upward displacement of the V-shaped plate 231. In this way, the positioning action of the abutment plate 236 on the stretcher beam in the bearing end 232 is guaranteed.

[0033] Furthermore, it can be understood that because the damping spring 213 is not compressed to its maximum, the vibration generated during flight will be buffered by the elastic damping deformation of the damping spring 213, preventing the injured from suffering secondary injuries during flight transfer. At the same time, the design of the above scheme allows the stretcher to be locked and unlocked in the cabin through simple actions, which greatly shortens the time for fixing and disassembling the stretcher in the cabin and effectively shortens the rescue time.

[0034] It should be noted that the specific models and specifications of the airborne mounting bracket 1, damping spring 213, return spring 313 and compression spring 338 need to be selected and determined according to the actual specifications of the device. The specific selection calculation method adopts the existing technology in this field, so it will not be described in detail.

[0035] The above embodiments are only used to illustrate specific implementations of the present invention and are not limited thereto. For those skilled in the art, various similar modifications and transformations can be made based on the concept of the present invention, and these modifications and transformations should all be considered within the scope of protection of the present invention.

Claims

1. A stretcher buffer and fixing structure for a helicopter airborne operation support subsystem, disposed on an airborne fixing frame (1) for supporting the stretcher, wherein a vertical frame (11) is fixedly connected to one side of the airborne fixing frame (1), and an upper fixing frame (12) is fixedly connected to the vertical frame (11), wherein the upper fixing frame (12) and the upper end face of the airborne fixing frame (1) are both used to support the stretcher, characterized in that: Four locking devices (2) are evenly arranged on the upper end face of the upper fixing frame (12) and the airborne fixing frame (1). The positions of the four locking devices (2) correspond to the four support points of the stretcher. The four locking devices (2) are exactly the same size. After the stretcher is placed on it, the locking device (2) will move downward and limit the stretcher from the top of the main beam of the stretcher, so that the stretcher will form an automatic locking action during the placement process. An unlocking device (3) is provided between the four locking devices (2). After the stretcher is placed on the locking device (2) without external force, the unlocking device (3) locks the displacement of the locking device (2) and prevents the locking device (2) from resetting. The unlocking device (3) releases its displacement lock on the locking device (2) by applying external force, thereby releasing the locking device (2) from the main beam of the stretcher, so that the stretcher can be removed from the locking device (2).

2. The stretcher buffer and fixing structure of the helicopter airborne operation support subsystem as described in claim 1, characterized in that, The locking device (2) includes a buffer assembly (21) fixed to the upper surface of the airborne mounting frame (1) and the upper mounting frame (12). A guide assembly (22) is fixed to the buffer assembly (21), and a positioning assembly (23) is slidably connected to the guide assembly (22). The positioning assembly (23) is connected to the buffer assembly (21).

3. The stretcher buffer and fixing structure for a helicopter airborne operation support subsystem as described in claim 2, characterized in that, The buffer component (21) includes: Positioning cylinder (211), the positioning cylinder (211) is fixed to the upper end face of the airborne fixing frame (1) and the upper fixing frame (12); A positioning shaft (212) is coaxially fixed to the bottom of the positioning cylinder (211); A damping spring (213) is sleeved on the positioning shaft (212).

4. The stretcher buffer and fixing structure for a helicopter airborne operation support subsystem as described in claim 3, characterized in that, The guide assembly (22) includes an L-shaped fixing plate (221) fixed to the top of the positioning cylinder (211). One end of the L-shaped fixing plate (221) is inclinedly fixed to an inclined plate (222). A hollow groove (223) is provided on the upper side of the inclined surface of the inclined plate (222). A first sliding groove (224) and a second sliding groove (225) are arranged side by side on both sides of the hollow groove (223). A positioning groove (226) is provided through the end of the L-shaped fixing plate (221) fixed to the inclined plate (222).

5. The stretcher buffer and fixing structure for a helicopter airborne operation support subsystem as described in claim 4, characterized in that, The positioning component (23) includes a V-shaped plate (231) disposed on the upper side of the L-shaped fixing plate (221). A V-shaped bearing end (232) is disposed on the upper side of the V-shaped plate (231). The bearing end (232) is used to support the main beam of the stretcher. A sliding shaft (233) is fixedly connected to the bottom end of the bearing end (232). The sliding shaft (233) slides through the L-shaped fixing plate (221) and is slidably inserted into the positioning cylinder (211). A guide cavity (234) is coaxially disposed inside the sliding shaft (233). The guide cavity (234) and the positioning shaft (212) are slidably connected. A connecting rod (235) is hinged to one end of the shaped plate (231) near the inclined plate (222), and an abutment plate (236) is hinged to the other end of the connecting rod (235). The abutment plate (236) is horizontally arranged and slidably arranged in the positioning groove (226). Two first sliding pins (237) and second sliding pins (238) are symmetrically fixed to both sides of the abutment plate (236). The first sliding pins (237) and the second sliding pins (238) slide in the first sliding groove (224) and the second sliding groove (225) respectively. The first sliding pins (237) and the connecting rod (235) are rotatably connected.

6. The stretcher buffer and fixing structure of the helicopter airborne operation support subsystem as described in claim 5, characterized in that, Two L-shaped fixing plates (221), two inclined plates (222) and two abutting plates (236) are symmetrically arranged at the same end of the airborne fixing frame (1), with the tops of the two inclined plates (222) being far apart from each other and the inner parts of the two abutting plates (236) being close to each other.

7. The stretcher buffer and fixing structure for a helicopter airborne operation support subsystem as described in claim 5, characterized in that, The unlocking device (3) includes: Two reset components (31) are arranged along the length of the airborne mounting frame (1); A pressure plate (32) is slidably disposed within the two reset components (31); Two connecting components (33) are respectively symmetrically arranged on both sides of the pressing plate (32) and are respectively slidably inserted into the four positioning slots (226).

8. The stretcher buffer and fixing structure of the helicopter airborne operation support subsystem as described in claim 7, characterized in that, The reset assembly (31) includes a positioning frame (311) fixed to the upper surface of the airborne mounting frame (1) and the upper mounting frame (12). Guide rods (312) are fixed to the top and bottom ends of the positioning frame (311). A reset spring (313) is sleeved on the guide rod (312). The pressing plate (32) is slidably sleeved on the guide rod (312) and pressed against the top of the reset spring (313).

9. The stretcher buffer and fixing structure of a helicopter airborne operation support subsystem as described in claim 7, characterized in that, A pressing block (321) is provided at the center of the bottom side of the pressing plate (32), and a first inclined surface (322) is symmetrically provided on both sides of the pressing block (321).

10. The stretcher buffer and fixing structure for a helicopter airborne operation support subsystem as described in claim 9, characterized in that, The connecting assembly (33) includes a first support rod (331) disposed on one side of the bottom of the pressing plate (32). A second support rod (332) is fixedly connected to the side of the first support rod (331) away from the pressing plate (32). Two L-shaped rods (333) are symmetrically fixed to both ends of the second support rod (332). A second inclined surface (334) that fits with the first inclined surface (322) is provided on the side of the first support rod (331) facing the pressing block (321). 31) A fixed block (335) is slidably sleeved on the upper part. The fixed block (335) is fixedly connected to the upper end face of the airborne fixed frame (1) and the upper fixed frame (12). A sliding block (336) is fixedly sleeved on the first support rod (331). A sliding rod (337) is fixedly connected to one side of the sliding block (336). The sliding rod (337) is slidably inserted into the fixed block (335). A compression spring (338) is sleeved on the sliding rod (337) and abuts against the fixed block (335).

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