Anti-impact aviation case based on carbon fiber composite material

Abstract

The utility model provides an anti-impact aviation case based on a carbon fiber composite material, and the aviation case comprises a case body, the top of the case body is rotatably connected with a cover plate, and the bottom of the inner side surface of the case body is provided with a plurality of threaded holes; and the multiple clamping frames are arranged on the inner side face of the box body, grooves are formed in the bottoms of the inner side faces of the multiple clamping frames, and locking screws are arranged on the inner side faces of the grooves. According to the anti-impact aviation case based on the carbon fiber composite material provided by the utility model, a plurality of structures such as the case body, the plurality of clamping frames and the clamping assemblies are matched with one another, so that when the anti-impact aviation case is used, a user can adaptively mount the clamping frames on the inner side surface of the case body according to the sizes and the number of articles; and then the rotating ring is rotated to drive the threaded ring to be in threaded connection with the outer side face of the extending rod, then the clamping plates clamp the objects, in this way, the multiple objects can be stored and transferred at the same time, and the space utilization rate is increased.

Description

Technical Field

[0001] The utility model relates to the technical field of transportation equipment, in particular to an impact-resistant aviation box based on carbon fiber composite materials. Background Art

[0002] With the rapid development of the air transportation industry, the requirements for the safety and reliability of cargo transportation are increasing day by day. In air transportation, various precision instruments, valuables, fragile items, etc. need special protection to prevent damage from impacts, vibrations, and other external forces during transportation.

[0003] For example, in the patent application with the publication number CN220663338U in the prior art, a lock shell is welded to the front of the box body, a lock core is rotatably connected to the front of the box cover, a fixed block is fixedly installed on the outside of the box body, a soft package is arranged inside the fixed block, a servo motor is arranged inside the box body, the output end of the servo motor is fixedly connected to a bidirectional screw, a screw block is threadedly connected to the outside of the bidirectional screw, a pressing plate is fixedly installed on the upper side of the screw block, a pressing pad is fixedly installed inside the pressing plate, and a partition board is arranged directly above the servo motor. By using the pressing plate to limit and fix the left and right sides of the aviation box, when the aviation box is impacted, the items will not move inside the box under the action of inertia and will not impact the inner wall of the aviation box, ensuring that the items will not be damaged or damaged due to collision and improving the overall impact resistance of the aviation box.

[0004] However, when this box body is in use, only a single item can be loaded during a single transportation, which easily causes a large waste of the internal space of the box body, thereby reducing the space utilization rate.

[0005] Therefore, it is necessary to provide an impact-resistant aviation box based on carbon fiber composite materials to solve the above technical problems. Summary of the Utility Model

[0006] The utility model provides an impact-resistant aviation box based on carbon fiber composite materials, which solves the problems of waste of the internal space of the box body and reduction of the space utilization rate.

[0007] To solve the above technical problems, an impact-resistant aviation box based on carbon fiber composite materials provided by the utility model includes:

[0008] A box body, the top of the box body is rotatably connected with a cover plate, and a plurality of threaded holes are opened at the bottom of the inner side surface of the box body;

[0009] A plurality of clamping frames, all of the plurality of clamping frames are arranged on the inner side surface of the box body, grooves are opened at the bottoms of the inner side surfaces of the plurality of clamping frames, and locking screws are arranged on the inner side surfaces of the grooves;

[0010] Clamping assembly, the clamping assemblies are respectively fixedly installed on both sides of the inner side surfaces of a plurality of clamping frames. The clamping assembly includes a fixed rod, an extension rod is slidably connected to the inner side surface of the fixed rod, a clamping plate is fixedly installed at one end of the extension rod, a rubber pad is fixedly installed on one side of the clamping plate, one end of the outer side surface of the fixed rod is rotatably connected to a rotating ring, a threaded ring is fixedly installed on the inner side surface of the rotating ring, and the threaded ring is threadedly connected to the outer side surface of the extension rod.

[0011] Preferably, limiting grooves are formed on both sides of the extension rod, limiting blocks are slidably connected to the inner side surfaces of the limiting grooves, and the limiting blocks are respectively fixedly installed on both sides of the inner side surface of the fixed rod.

[0012] Preferably, soft packages are sleeved on the outer side surfaces of the box body and the cover plate, and lock catches are arranged at both ends of one side of the box body and the cover plate.

[0013] Preferably, the bottom of the locking screw is threadedly connected to the inner side surface of the threaded hole.

[0014] Preferably, the front and back surfaces of the clamping frame are respectively attached to the front and back surfaces of the inner side surface of the box body.

[0015] Preferably, sponge pads are arranged on both sides of the groove.

[0016] Preferably, the sponge pads are arranged at the bottom of the inner side surface of the clamping frame.

[0017] Compared with the related art, a shock-proof aviation box based on carbon fiber composite material provided by the present utility model has the following beneficial effects:

[0018] The present utility model provides a shock-proof aviation box based on carbon fiber composite material. Through the cooperation of multiple structures such as the box body, a plurality of clamping frames and clamping assemblies, when in use, the user can adaptively install the clamping frames on the inner side surface of the box body according to the size and quantity of the items, and then drive the threaded ring to be threadedly connected to the outer side surface of the extension rod by rotating the rotating ring, and then the clamping plate clamps the items. In this way, multiple items can be stored and transported at the same time, increasing the space utilization rate. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 is a schematic structural diagram of the first embodiment of a shock-proof aviation box based on carbon fiber composite material provided by the present utility model;

[0020] Figure 2 is Figure 1 the schematic structural diagram of the box body shown;

[0021] Figure 3 isFigure 1 Schematic diagram of the top view cross-section structure of the clamping assembly shown;

[0022] Figure 4 is Figure 2 Enlarged schematic diagram of part A shown;

[0023] Figure 5 Schematic diagram of the structure of the second embodiment of an impact-resistant aviation box based on carbon fiber composite material provided by the present utility model.

[0024] Reference numerals in the figure: 1, box body; 11, cover plate; 12, lock; 13, threaded hole; 2, clamping frame; 21, groove; 22, locking screw; 3, clamping assembly; 31, fixed rod; 32, extension rod; 33, limiting groove; 34, limiting block; 35, rotating ring; 36, threaded ring; 37, clamping plate; 38, rubber pad; 4, surrounding plate; 41, sealing pad; 5, soft package; 6, sponge pad. Detailed implementation manners

[0025] The present utility model will be further described below in conjunction with the accompanying drawings and embodiments.

[0026] First embodiment

[0027] Please refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 , wherein, Figure 1 Schematic diagram of the structure of the first embodiment of an impact-resistant aviation box based on carbon fiber composite material provided by the present utility model; Figure 2 is Figure 1 Schematic diagram of the box body structure shown; Figure 3 is Figure 1 Schematic diagram of the top view cross-section structure of the clamping assembly shown;

[0028] Figure 4 is Figure 2 Enlarged schematic diagram of part A shown. An impact-resistant aviation box based on carbon fiber composite material, comprising: a box body 1, a cover plate 11 is rotatably connected to the top of the box body 1, and a plurality of threaded holes 13 are opened at the bottom of the inner side surface of the box body 1;

[0029] A plurality of clamping frames 2, the plurality of clamping frames 2 are all arranged on the inner side surface of the box body 1, grooves 21 are opened at the bottoms of the inner side surfaces of the plurality of clamping frames 2, and locking screws 22 are arranged on the inner side surfaces of the grooves 21;

[0030] The clamping assembly 3 is respectively and fixedly installed on both sides of the inner side surfaces of a plurality of clamping frames 2. The clamping assembly 3 includes a fixed rod 31. A telescopic rod 32 is slidably connected to the inner side surface of the fixed rod 31. A clamping plate 37 is fixedly installed at one end of the telescopic rod 32. A rubber pad 38 is fixedly installed on one side of the clamping plate 37. One end of the outer side surface of the fixed rod 31 is rotatably connected to a rotating ring 35. A threaded ring 36 is fixedly installed on the inner side surface of the rotating ring 35. The threaded ring 36 is threadedly connected to the outer side surface of the telescopic rod 32.

[0031] Limit grooves 33 are respectively formed on both sides of the telescopic rod 32. A limit block 34 is slidably connected to the inner side surface of the limit groove 33. The limit blocks 34 are respectively fixedly installed on both sides of the inner side surface of the fixed rod 31.

[0032] Soft packages 5 are sleeved on the outer side surfaces of the box body 1 and the cover plate 11. Lock catches 12 are arranged at both ends of one side of the box body 1 and the cover plate 11.

[0033] The bottom of the locking screw 22 is threadedly connected to the inner side surface of the threaded hole 13.

[0034] The front and back surfaces of the clamping frame 2 are respectively attached to the front and back surfaces of the inner side surface of the box body 1.

[0035] Both the box body 1 and the cover plate 11 are made of carbon fiber composite materials. In this way, not only the impact resistance strength of the box body 1 and the cover plate 11 can be increased, but also the weight can be reduced.

[0036] By arranging the soft packages 5 on the outer side surfaces of the box body 1 and the cover plate 11, during use, it can play a role in protecting the outer side surfaces of the box body 1 and the cover plate 11, avoiding abrasion of the box body 1 and the cover plate 11 caused by stacking with other box bodies 1 during the transportation process.

[0037] When the cover plate 11 covers the top of the box body 1, the surrounding plate 4 will be inserted into the inner side surface of the cover plate 11. At this time, the bottom of the cover plate 11 will press on the top of the sealing gasket 41, so as to play a sealing role and prevent rainwater from entering the inner side surface of the box body 1.

[0038] The working principle of an impact-resistant aviation box based on carbon fiber composite materials provided by the present utility model is as follows:

[0039] When in use, the user can install the clamping frame 2 adaptively according to the size and quantity of the items. Place the clamping frame 2 on the inner side of the box body 1, then insert the locking screw 22 into the inner side of the groove 21, and thread the bottom of the locking screw 22 onto the inner side of the threaded hole 13. Then, clamp and limit the clamping frame 2. After that, the user puts the items to be stored into the inner side of the box body 1 and in the middle of the two clamping components 3. Then the user rotates the rotating ring 35, so that the rotating ring 35 drives the threaded ring 36 to be threadedly connected to the outer side of the extension rod 32. Then the extension rod 32 drives the clamping plate 37 and the rubber pad 38 to move towards one side of the item, so that the clamping plate 37 and the rubber pad 38 cooperate with each other to clamp and limit the item.

[0040] Compared with the related technology, a shock-proof aviation box based on carbon fiber composite material provided by the present utility model has the following beneficial effects:

[0041] Through the cooperation of multiple structures such as the box body 1, multiple clamping frames 2 and clamping components 3, when in use, the user can adaptively install the clamping frame 2 on the inner side of the box body 1 according to the size and quantity of the items. Then, by rotating the rotating ring 35, the threaded ring 36 is threadedly connected to the outer side of the extension rod 32. After that, the clamping plate 37 clamps the item, so that multiple items can be stored and transported at the same time, increasing the space utilization rate.

[0042] Second Embodiment

[0043] Please refer to Figure 5 , based on a shock-proof aviation box made of carbon fiber composite material provided in the first embodiment of the present application, the second embodiment of the present application proposes another shock-proof aviation box made of carbon fiber composite material. The second embodiment is only a preferred way of the first embodiment, and the implementation of the second embodiment will not affect the independent implementation of the first embodiment.

[0044] Specifically, the difference of a shock-proof aviation box made of carbon fiber composite material provided in the second embodiment of the present application is that sponge pads 6 are arranged on both sides of the groove 21.

[0045] The sponge pads 6 are arranged at the bottom of the inner side of the clamping frame 2.

[0046] The working principle of a shock-proof aviation box made of carbon fiber composite material provided by the present utility model is as follows:

[0047] When in use, the user places the items to be stored and transported on the sponge pads 6, and then the user clamps and limits the items through the clamping components 3.

[0048] Compared with the related technologies, a shock-proof aviation box based on carbon fiber composite materials provided by the present utility model has the following beneficial effects:

[0049] By installing a sponge pad 6 at the bottom of the inner side of the clamping frame 2, when storing items, the bottom of the items can be prevented from directly rubbing against the bottom of the inner side of the clamping frame 2, thereby playing a role in protecting the items.

[0050] The above are only the embodiments of the present utility model, and thus do not limit the patent scope of the present utility model. Any equivalent structure or equivalent process transformation made by using the specification and drawings of the present utility model, or directly or indirectly applied in other related technical fields, shall be similarly included in the patent protection scope of the present utility model.

Claims

1. An impact-resistant aviation box based on carbon fiber composite material, characterized in that: include: A box body, the top of which is rotatably connected to a cover plate, and the bottom of the inner side of the box body is provided with a plurality of threaded holes; A plurality of clamping frames, each of which is arranged on the inner side of the box body, each of which has a groove at the bottom of the inner side, and a locking screw is arranged on the inner side of the groove; A clamping assembly, wherein the clamping assemblies are respectively fixedly installed on both sides of the inner sides of multiple clamping frames, the clamping assembly includes a fixed rod, the inner side of the fixed rod is slidably connected to an extension rod, one end of the extension rod is fixedly installed with a clamping plate, one side of the clamping plate is fixedly installed with a rubber pad, one end of the outer side of the fixed rod is rotatably connected with a rotating ring, the inner side of the rotating ring is fixedly installed with a threaded ring, and the threaded ring is threadedly connected to the outer side of the extension rod.

2. The impact-resistant aviation box based on carbon fiber composite material according to claim 1, characterized in that: Limiting grooves are provided on both sides of the extension rod, and the inner side surfaces of the limiting grooves are slidably connected to limiting blocks, and the limiting blocks are respectively fixedly installed on both sides of the inner side surface of the fixing rod.

3. The impact-resistant aviation box based on carbon fiber composite material according to claim 2, characterized in that: The outer sides of the box body and the cover plate are both covered with soft bags, and both ends of one side of the box body and the cover plate are both provided with lock buckles.

4. The impact-resistant aviation box based on carbon fiber composite material according to claim 3, characterized in that: The bottom of the locking screw is threadedly connected to the inner side surface of the threaded hole.

5. The impact-resistant aviation box based on carbon fiber composite material according to claim 4, characterized in that: The front and back sides of the clamping frame are respectively attached to the front and back sides of the inner side surfaces of the box body.

6. The impact-resistant aviation box based on carbon fiber composite material according to claim 1, characterized in that: Sponge pads are arranged on both sides of the groove.

7. The impact-resistant aviation box based on carbon fiber composite material according to claim 6, characterized in that: The sponge pad is arranged at the bottom of the inner side surface of the clamping frame.

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