Packaging box for transporting airplane parts
By using composite material boxes and lids, combined with removable linings and limiting structures, the problems of heavy weight and poor corrosion resistance of existing packaging boxes have been solved, achieving lightweight and durability, ensuring the safety and flexible adaptability of aircraft parts during transportation, and meeting the high standards of modern air transport.
Patent Information
- Application Number
- CN202520281119.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-21
- Publication Date
- 2025-11-25
- Estimated Expiration
- 2035-02-21
AI Technical Summary
Existing aircraft parts packaging boxes are heavy, have poor corrosion resistance, short service life, and are prone to damage during transportation due to size mismatch, making it difficult to meet the high standards required by modern air transport.
The use of composite material for the housing and lid, combined with a removable liner and limiting structure, enhances connection stability and flexibility. The removable liner matches the components, reducing displacement and collision.
It achieves lightweight, corrosion-resistant, and long-lasting packaging boxes, ensuring safety and flexibility during transportation and meeting the high standards of modern air transport.
Smart Images
Figure CN223591466U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of transportation equipment technology, specifically relating to a packaging box for transporting aircraft parts. Background Technology
[0002] With the rapid development of my country's aviation industry, the demand for the transfer of aircraft parts has increased significantly. However, aircraft parts, especially large components, require large packaging boxes during transfer due to their large size and complex structure. Currently, these boxes are mostly made of metal or wood, which suffers from problems such as heavy weight, poor corrosion resistance, and short service life. This not only affects the convenience of transfer but also limits their reusability. Furthermore, existing packaging boxes are usually equipped with integrated padding, which causes inconvenience when the padding needs to be replaced or the packaging size adjusted according to specific needs. More importantly, because the packaging box size does not match the actual size of the parts, the parts are prone to displacement or collision during transportation, resulting in damage and affecting transfer efficiency. These problems make it difficult for current packaging technology to meet the high standards required by modern air transport.
[0003] The information disclosed in this background section is intended only to enhance the understanding of the overall background of this utility model and should not be construed as an admission or in any way implying that the information constitutes prior art known to those skilled in the art. Utility Model Content
[0004] The purpose of this utility model is to provide a packaging box for transporting aircraft parts, which can solve the technical problems mentioned in the background art.
[0005] To achieve the above objectives, the technical solution provided by a specific embodiment of this utility model is as follows:
[0006] A packaging box for transporting aircraft parts includes a composite material box body and a composite material box lid, which are detachably connected. A box body liner assembly is installed inside the composite material box body, and the box body liner assembly includes multiple second soft liners that are snapped into the composite material box body. A box lid liner assembly is installed inside the composite material box lid, and the box lid liner assembly includes multiple first soft liners that are snapped into the composite material box lid. Limiting blocks are provided on the inner walls of both the composite material box body and the composite material box lid. Second limiting grooves matching the limiting blocks are formed on the second soft liners, and multiple first limiting grooves matching the limiting blocks are formed on the first soft liners.
[0007] In one or more embodiments of this utility model, an isolation liner is further provided between the lid liner assembly and the body liner assembly, and the two ends of the isolation liner are in contact with the lid liner assembly and the body liner assembly, respectively.
[0008] In one or more embodiments of this utility model, a second reinforcing rib and a third reinforcing rib are fixedly connected to both the composite material box body and the composite material box cover. The second reinforcing rib and the third reinforcing rib are integrally formed on the outer wall of the composite material box body and the composite material box cover. The direction in which the second reinforcing rib is set is perpendicular to the direction in which the third reinforcing rib is set.
[0009] In one or more embodiments of this utility model, multiple anti-collision blocks are fixedly connected to the outer walls of the composite material box body and the composite material box cover, and the multiple anti-collision blocks are integrally formed on the second reinforcing rib and the third reinforcing rib respectively.
[0010] In one or more embodiments of this utility model, a first reinforcing rib is fixedly connected to both the composite material box body and the composite material box cover. The first reinforcing rib is located at one end of the composite material box body near the composite material box cover and at one end of the composite material box cover near the composite material box body.
[0011] In one or more embodiments of this utility model, a buckle is fixedly connected to the outer wall of the composite material box body, and a fastener matching the buckle is fixedly connected to the outer wall of the composite material box cover. The buckle is fixedly connected to the first reinforcing rib of the composite material box body, and the fastener is fixedly connected to the first reinforcing rib of the composite material box cover.
[0012] In one or more embodiments of this utility model, a placement groove is provided on one of the first reinforcing ribs, and a sealing ring is placed in the placement groove.
[0013] In one or more embodiments of this utility model, a plurality of first connectors are fixedly connected to the composite material box body, and the first connectors are provided with connection holes. A second connector is fixedly connected to the composite material box cover, and a connecting post matching the connection hole is fixedly connected to the second connector. The first connectors are fixedly connected to the first reinforcing rib of the composite material box body, and the second connectors are fixedly connected to the first reinforcing rib of the composite material box cover.
[0014] In one or more embodiments of this utility model, the inner walls of the connecting post and the connecting hole are interference fit.
[0015] In one or more embodiments of this utility model, a stacking positioning platform is fixedly connected to the composite material box body, and the second and third reinforcing ribs on the composite material box cover form grooves that match the stacking positioning platform.
[0016] Compared with the prior art, the packaging box for transporting aircraft parts of this utility model adopts a composite material box body and a composite material box lid, which can reduce the weight of the packaging box and improve its corrosion resistance and service life, which is beneficial for transporting aircraft parts. In addition, the use of a removable liner can be replaced according to the shape of the parts, which can avoid the situation where the liner does not match the parts and thus cause damage to the aircraft parts, and helps to meet the high standards of modern air transport. Attached Figure Description
[0017] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0018] Figure 1 This is a schematic diagram of the structure of a packaging box for transporting aircraft parts according to one embodiment of the present invention. Figure 1 ;
[0019] Figure 2 for Figure 1 Schematic diagram of the structure at point A in the middle;
[0020] Figure 3 for Figure 2 Schematic diagram of the structure at point B;
[0021] Figure 4 This is a schematic diagram of the structure of a packaging box for transporting aircraft parts according to one embodiment of the present invention. Figure 2 ;
[0022] Figure 5 This is an exploded view of a packaging box for transporting aircraft parts according to one embodiment of the present invention;
[0023] Figure 6 This is a schematic diagram of the composite material box body in one embodiment of the present invention;
[0024] Figure 7 This is a schematic diagram of the composite material box cover in one embodiment of the present invention;
[0025] Figure 8 This is a schematic diagram of the structure of the box body liner assembly, the box cover liner assembly, and the isolation liner in one embodiment of the present invention.
[0026] Explanation of key figure labels:
[0027] 1. Composite material box body; 2. First reinforcing rib; 201. Placement groove; 3. Second reinforcing rib; 4. Third reinforcing rib; 5. Composite material box cover; 6. Buckle; 7. Fastener; 8. Anti-collision block; 9. First connector; 901. Connecting hole; 10. Second connector; 11. Connecting column; 12. First lifting ring; 13. Second lifting ring; 14. Stacking positioning platform; 15. Limiting block; 16. Box cover padding assembly; 17. First soft padding; 1701. First limiting groove; 18. Box body padding assembly; 19. Second soft padding; 1901. Second limiting groove; 20. Isolation padding. Detailed Implementation
[0028] To enable those skilled in the art to better understand the technical solutions of this utility model, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of this utility model.
[0029] like Figures 1-2 As shown, a packaging box for transporting aircraft parts according to one embodiment of this utility model includes a composite material box body 1 and a composite material box lid 5. Multiple second reinforcing ribs 3 and multiple third reinforcing ribs 4 are fixedly connected to both the composite material box body 1 and the composite material box lid 5. The second reinforcing ribs 3 and third reinforcing ribs 4 are integrally formed on the composite material box body 1 and the composite material box lid 5, and are arranged along the outer wall of the composite material box body 1 and the composite material box lid 5, with the directions of the second reinforcing ribs 3 and the third reinforcing ribs 4 being perpendicular to each other. The provision of second reinforcing ribs 3 and third reinforcing ribs 4 can reduce the thickness of the composite material box body 1 and the composite material box lid 5, while simultaneously increasing their strength.
[0030] The composite material box body 1 and the composite material box cover 5 are made of one or more of the following: carbon fiber reinforced composite material, glass fiber reinforced composite material, aramid fiber reinforced composite material, honeycomb sandwich composite material, polyether ether ketone (PEEK) composite material, and ultra-high molecular weight polyethylene (UHMWPE) composite material.
[0031] like Figures 1-4As shown, first reinforcing ribs 2 are fixedly connected to the contact surfaces of the composite material box body 1 and the composite material box cover 5. The first reinforcing ribs 2 are integrally formed on the composite material box body 1 and the composite material box cover 5. The first reinforcing ribs 2 increase the strength of the connection between the composite material box body 1 and the composite material box cover 5, minimizing deformation at the connection point due to heavy object compression, which could affect the sealing effect of the composite material box body 1 and the composite material box cover 5. This ensures the sealing and safety of the aircraft parts packaged in the composite material box body 1 and the composite material box cover 5 as much as possible.
[0032] like Figures 1-2 As shown, the composite material box body 1 and the composite material box cover 5 are detachable. A buckle 6 is fixedly connected to the first reinforcing rib 2 of the composite material box body 1, and a fastener 7 is fixedly connected to the first reinforcing rib 2 of the composite material box cover 5. The buckle 6 and the fastener 7 can be engaged. This makes the connection between the composite material box body 1 and the composite material box cover 5 tighter and minimizes the possibility of the composite material box body 1 and the composite material box cover 5 separating during transportation.
[0033] To further improve the sealing performance at the connection between the composite material box body 1 and the composite material box cover 5, such as Figure 6 As shown, a placement groove 201 is provided on the end face of the first reinforcing rib 2 on the composite material box body 1 and the first reinforcing rib 2 on the composite material box cover 5, and a sealing ring (not shown in the figure) is snapped onto the placement groove 201.
[0034] like Figures 1-3 As shown, a first connector 9 is fixedly connected to the first reinforcing rib 2 of the composite material box body 1. The first connector 9 has a connecting hole 901. A second connector 10 is fixedly connected to the first reinforcing rib 2 of the composite material box cover 5. The second connector 10 has a connecting hole 901 that matches the connecting post 11. The connecting post 11 is inserted into the connecting hole 901, which can realize the positioning of the composite material box body 1 and the composite material box cover 5 when they are combined, and avoid the situation where the packaging box is unstable due to misalignment of the composite material box body 1 and the composite material box cover 5. It can also temporarily fix the composite material box body 1 and the composite material box cover 5 through the second connector 10 and the first connector 9 during temporary packaging and transportation, so as to realize short-distance transportation.
[0035] like Figures 1-4 As shown, multiple stacking positioning platforms 14 are fixedly connected to the outer wall of the composite material box 1. The second reinforcing rib 3 and the third reinforcing rib 4 on the composite material box cover 5 form a snap-fit groove that matches the stacking positioning platform 14, and the stacking positioning platform 14 snaps into the snap-fit groove. When the packaging boxes are stacked, it is not easy for multiple packaging boxes to shift.
[0036] like Figures 1-4As shown, multiple first lifting rings 12 are fixedly connected to the composite material box cover 5, which can be used to lift the packaging box.
[0037] like Figures 1-4 As shown, multiple second lifting rings 13 are fixedly connected to the side walls of the composite material box body 1 and the composite material box cover 5, respectively. The multiple second lifting rings 13 are all fixedly connected to the second reinforcing ribs 3. The packaging box can also be lifted by the second lifting rings 13. The second lifting rings 13 are fixed to the second reinforcing ribs 3. During the lifting process, the tension generated is applied to the second reinforcing ribs 3, which makes it less likely for the packaging box to deform.
[0038] like Figures 1-4 As shown, multiple anti-collision blocks 8 are fixedly connected to the side walls of the composite material box body 1 and the composite material box cover 5. These anti-collision blocks 8 are respectively fixedly connected to the third reinforcing rib 4. Similarly, the anti-collision blocks 8 can reduce damage to the packaging box during impact. The anti-collision blocks 8 are fixedly connected to the third reinforcing rib 4. When the packaging box is impacted, the third reinforcing rib 4 bears a large amount of force, reducing the force borne by the composite material box body 1 and the composite material box cover 5, and minimizing the possibility of deformation of the composite material box body 1 and the composite material box cover 5 leading to damage to the packaging box.
[0039] like Figures 5-8 As shown, a box liner assembly 18 is installed inside the composite material box 1. The box liner assembly 18 consists of multiple second soft liners 19, which are installed inside the composite material box 1 by splicing. A box cover liner assembly 16 is installed inside the composite material box cover 5. The box cover liner assembly 16 consists of multiple first soft liners 17, which are installed inside the composite material box cover 5 by splicing. By installing the box cover liner assembly 16 and the box liner assembly 18 by splicing, the box cover liner assembly 16 and the box liner assembly 18 can be replaced when handling different aircraft parts, so that the box cover liner assembly 16 and the box liner assembly 18 match the aircraft parts, thereby reducing the possibility of aircraft parts shaking and being bumped during transportation inside the packaging box.
[0040] like Figures 5-8As shown, multiple limiting blocks 15 are fixedly connected to the inner walls of the composite material box 1 and the composite material box cover 5. A second limiting groove 1901 matching the limiting block 15 inside the composite material box 1 is provided on the second soft pad 19, and a first limiting groove 1701 matching the limiting block 15 inside the composite material box cover 5 is provided on the first soft pad 17. The second soft pad 19 can be engaged with the limiting block 15 on the composite material box 1 through the second limiting groove 1901, allowing the limiting block 15 to provide simple positioning for the second soft pad 19 during assembly of the composite material box 1. Similarly, the first soft pad 17 is engaged with the limiting block 15 on the composite material box cover 5 through the first limiting groove 1701, allowing the limiting block 15 to provide simple positioning for the first soft pad 17 during assembly.
[0041] like Figures 5-8 As shown, an isolation pad 20 is installed between the box body padding assembly 18 and the box lid padding assembly 16. The two ends of the isolation pad 20 are clamped by the box lid padding assembly 16 and the box body padding assembly 18 respectively, which realizes the separation inside the packaging box and can also achieve a certain shock absorption effect, thus protecting the parts.
[0042] In use, firstly, a second soft pad 19 is spliced inside the composite material box 1, and a first soft pad 17 is spliced inside the composite material box cover 5. The inner walls of the composite material box 1 and the composite material box cover 5 are wrapped by the second soft pad 19 and the first soft pad 17, allowing aircraft parts to be installed inside the composite material box 1 and the composite material box cover 5 respectively. The second soft pad 19 and the first soft pad 17 provide protection for the aircraft parts. Then, the composite material box 1 and the composite material box cover 5 are assembled. During assembly, the connecting post 11 needs to be aligned with the connecting hole 901, and the connecting post 11 is inserted into the connecting hole 901. The connecting post 11 and the connecting hole 901 are interference-fitted for simple fixation. Finally, the buckle 6 and the fastener 7 are overlapped.
[0043] This invention employs a detachable box liner assembly 18 and a box cover liner assembly 16, which can be matched to aircraft parts to ensure the safety of aircraft parts during transportation as much as possible. The use of composite materials also meets the performance requirements of being lightweight, maintenance-free, having a long service life, being easy to use, and being reusable multiple times.
[0044] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.
[0045] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.
Claims
1. A shipping container for aircraft parts, comprising: include: The composite material box body and the composite material box cover are detachably connected; The composite material box is equipped with a box liner assembly, which includes multiple second soft liners that are snapped into the composite material box. The composite material box lid is equipped with a lid liner assembly, which includes multiple first soft liners that are snapped into the composite material box lid. The inner walls of both the composite material box and the composite material box lid are provided with limit blocks. The second soft liners have second limit grooves that match the limit blocks, and the first soft liners have multiple first limit grooves that match the limit blocks.
2. A shipping container for aircraft parts as defined in claim 1, wherein, An isolation pad is also provided between the lid pad assembly and the body pad assembly, with both ends of the isolation pad contacting the lid pad assembly and the body pad assembly, respectively.
3. The shipping container of claim 1, wherein, The composite material box body and the composite material box cover are both fixedly connected with a second reinforcing rib and a third reinforcing rib. The second reinforcing rib and the third reinforcing rib are integrally formed on the outer wall of the composite material box body and the composite material box cover. The direction of the second reinforcing rib is perpendicular to the direction of the third reinforcing rib.
4. The shipping container of claim 2, wherein, Multiple anti-collision blocks are fixedly connected to the outer walls of the composite material box body and the composite material box cover. The multiple anti-collision blocks are integrally formed on the second reinforcing rib and the third reinforcing rib respectively.
5. The shipping container of claim 1, wherein, Both the composite material box body and the composite material box cover are fixedly connected with a first reinforcing rib, which is located at the end of the composite material box body near the composite material box cover and the end of the composite material box cover near the composite material box body.
6. A packaging box for transporting aircraft parts according to claim 5, characterized in that A buckle is fixedly connected to the outer wall of the composite material box body, and a fastener matching the buckle is fixedly connected to the outer wall of the composite material box cover. The buckle is fixedly connected to the first reinforcing rib of the composite material box body, and the fastener is fixedly connected to the first reinforcing rib of the composite material box cover.
7. A packaging box for transporting aircraft parts according to claim 5 or 6, characterized in that One of the first reinforcing ribs has a placement groove, and a sealing ring is placed in the placement groove.
8. A packaging box for transporting aircraft parts according to claim 7, characterized in that Multiple first connectors are fixedly connected to the composite material box body. Each first connector has a connection hole. A second connector is fixedly connected to the composite material box cover. A connecting post matching the connection hole is fixedly connected to the second connector. The first connector is fixedly connected to the first reinforcing rib of the composite material box body, and the second connector is fixedly connected to the first reinforcing rib of the composite material box cover.
9. A packaging box for transporting aircraft parts according to claim 8, characterized in that The inner walls of the connecting column and the connecting hole are interference fit.
10. The shipping container of claim 1, wherein, A stacking positioning platform is fixedly connected to the composite material box body, and the second and third reinforcing ribs on the composite material box cover form grooves that match the stacking positioning platform.