Drop-resistant container structure

Abstract

The application discloses an anti-falling container structure, which comprises a spherical tank body, an upper energy-absorbing assembly arranged at the top of the spherical tank body, and a lower energy-absorbing assembly arranged at the bottom of the spherical tank body; the top of the upper energy-absorbing assembly is connected with a structural top plate of an aircraft, and the bottom of the lower energy-absorbing assembly is connected with a structural bottom plate of the aircraft; a plurality of tensioning assemblies for positioning and tightening the spherical tank body are connected between the upper energy-absorbing assembly and the lower energy-absorbing assembly; the application limits the movement of the whole spherical tank body in the axial direction of the base, thereby playing an anti-falling role; meanwhile, the application has simple structure, small installation space requirement and wide applicability.

Description

Technical Field

[0001] This invention relates to the field of aircraft structure, and more particularly to a crash-resistant container structure. Background Technology

[0002] Currently, the design concept of using hydrogen energy as a power source in the aviation field is becoming more active. High-pressure liquefied hydrogen is stored in containers, typically large spherical tanks, installed inside aircraft. To meet aviation safety requirements, these spherical containers need to be designed to withstand crashes.

[0003] Among the existing structures most similar to this application for fixing spherical containers, there is a composite wind-damping and vibration reduction device (authorization announcement number CN218543040U). In this solution, the system constraints are insufficient, the vibration freedom is too high, and a large installation space is required, which creates additional crash risk in the crowded aircraft structure design. In another solution, there is a spherical storage tank for UAVs (authorization announcement number CN202211400486). In this solution, the spherical container is fixed at the top and bottom with an annular support plate and tie rod. Due to the curvature of the container, the tie rod is not fully fitted with the spherical container, and the outward extension creates additional crash risk.

[0004] Therefore, this application proposes a solution to address the need for anti-collision measures for spherical containers. Summary of the Invention

[0005] Purpose of the invention: The purpose of this invention is to provide a crash-resistant container structure that can prevent containers storing hydrogen energy in aircraft from shaking and colliding when encountering turbulence during flight, thereby avoiding safety accidents.

[0006] Technical solution: The impact-resistant container structure of the present invention includes a spherical tank. An upper energy-absorbing component is provided at the top of the spherical tank, and a lower energy-absorbing component is provided at the bottom. The top of the upper energy-absorbing component is connected to the top plate of the aircraft structure, and the bottom of the lower energy-absorbing component is connected to the bottom plate of the aircraft structure. Multiple tensioning components are connected between the upper and lower energy-absorbing components to position and tighten the spherical tank.

[0007] Preferably, the upper energy-absorbing assembly includes an upper support plate, hinges, hinge seats, springs, and a ring. The bottom of the upper support plate is fitted to the top of the spherical tank. Multiple circumferentially distributed hinge seats are fixed to the top of the upper support plate. Hinges are connected to the multiple circumferentially distributed hinge seats. The top of the hinges is connected to the hinge seats fixed to the top plate of the aircraft structure. The middle of the multiple hinges is connected to the same ring through the springs.

[0008] Preferably, the upper support plate has a ring-shaped structure, and the ratio of the top area of ​​the spherical can covered by the upper support plate to the top area of ​​the spherical can is between 0 and 1 / 4. The distance between the plane containing the lower edge of the upper support plate and the top of the spherical can is between 0 and 1 / 3 of the radius of the spherical can.

[0009] Preferably, the upper support plate, the ring, and the spherical tank are concentric.

[0010] Preferably, the lower energy-absorbing component includes a lower support plate, a base, and a flexible energy-absorbing material. The base is a cylindrical structure and is fixed to the bottom of the aircraft structure. The lower support plate is disposed on the base and its top is connected to a spherical tank. The flexible energy-absorbing material is filled inside the base.

[0011] Preferably, the bottom of the lower support plate is provided with a cylinder that extends into the base and is in clearance fit with the base and the flexible energy-absorbing material. When vibrating, the cylinder moves up and down along the base like a piston.

[0012] Preferably, the top end face of the lower support plate is concave, concentric with the spherical tank and in contact with the bottom of the spherical tank, and the distance between the plane containing the upper edge of the lower support plate and the bottom of the spherical tank is between 0 and 1 / 4 of the radius of the spherical tank.

[0013] Preferably, hinge seats are provided in pairs on the bottom end face of the lower support plate and on the outer wall of the base, and the two hinge seats are connected by a spring.

[0014] Preferably, the hinge seat 2 provided on the bottom end face of the lower support plate is connected to the tensioning assembly.

[0015] Preferably, the tensioning assembly includes a buckle and an elastic band, with buckles connected to both ends of the elastic band, and the buckles are respectively connected to the upper energy-absorbing assembly and the lower energy-absorbing assembly.

[0016] Beneficial effects: Compared with the prior art, the present invention has the following significant advantages:

[0017] This invention secures the spherical tank within the aircraft while simultaneously controlling the vertical extension and retraction of the hinged suspension using a ring and spring. The relative piston movement between the cylinder of the lower support plate and the base restricts the movement of the entire spherical tank to the axial direction of the base, thus preventing crashes. Furthermore, this invention features a simple structure, requires minimal installation space, and has wide applicability. Attached Figure Description

[0018] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0019] Figure 2 This is a front view of the present invention.

[0020] Figure 3 This is a three-dimensional structural diagram of the upper energy-absorbing component in this invention.

[0021] Figure 4 This is a three-dimensional structural diagram of the lower energy-absorbing component in this invention.

[0022] Figure 5 This is a cross-sectional view of the lower energy-absorbing component in this invention.

[0023] Figure 6 This is a schematic diagram of the structure when the upper energy-absorbing component and the lower energy-absorbing component are connected together by a tensioning component in this invention.

[0024] Figure 7 This is an enlarged view of the upper energy-absorbing component and the tensioning component connected together in this invention.

[0025] The components include: 1. Spherical tank; 2. Upper energy-absorbing assembly; 3. Lower energy-absorbing assembly; 4. Tensioning assembly; 21. Upper support plate; 22. Hinge; 23. Hinge seat one; 24. Spring one; 25. Ring; 31. Lower support plate; 32. Base; 33. Flexible energy-absorbing material; 34. Cylinder; 35. Hinge seat two; 36. Spring two; 41. Buckle; 42. Elastic band. Detailed Implementation

[0026] The technical solution of the present invention will be further described below with reference to the accompanying drawings.

[0027] See appendix Figures 1-5 Figure 1 is a schematic diagram of the structure of the present invention. The present invention includes a spherical tank 1, an upper energy-absorbing component 2 is provided on the top of the spherical tank 1, and a lower energy-absorbing component 3 is provided on the bottom. The top of the upper energy-absorbing component 2 is connected to the top plate of the aircraft structure, and the bottom of the lower energy-absorbing component 3 is connected to the bottom plate of the aircraft structure. Four tensioning components 4 are connected between the upper energy-absorbing component 2 and the lower energy-absorbing component 3 to position and tighten the spherical tank 1.

[0028] In this embodiment, the upper energy-absorbing component 2 includes an upper support plate 21, hinges 22, hinge seats 23, springs 24, and a ring 25. The bottom of the upper support plate 21 is attached to the top of the spherical tank 1. Four circumferentially distributed hinge seats 23 are fixed to the top of the upper support plate 21. Each of the four circumferentially distributed hinge seats 23 is connected to a hinge 22. The top of the hinge 22 is connected to the hinge seat 23 fixed to the top plate of the aircraft structure. The four hinges 22 are connected to the same ring 25 through springs 24.

[0029] In this embodiment, the upper support plate 21 has a ring structure, and the top area of ​​the spherical can 1 covered by the upper support plate 21 accounts for 1 / 5 of the top area of ​​the spherical can 1. The distance between the plane where the lower edge of the upper support plate 21 is located and the top of the spherical can 1 is 1 / 4 of the radius of the spherical can 1.

[0030] In this embodiment, the upper support plate 21 and the ring 25 are concentric with the spherical tank 1.

[0031] In this embodiment, the lower energy-absorbing component 3 includes a lower support plate 31, a base 32, and a flexible energy-absorbing material 33. The base 32 is a cylindrical structure and is fixed to the bottom of the aircraft structure. The lower support plate 31 is disposed on the base 32, with its top fitting against the spherical tank 1. The flexible energy-absorbing material 33 is filled inside the base 32.

[0032] In this embodiment, a cylinder 34 is provided at the bottom of the lower support plate 31. The cylinder 34 extends into the base 32 and is in clearance fit with the base 32 and the flexible energy-absorbing material 33. When vibrating, the cylinder 34 moves up and down along the base 32 like a piston.

[0033] In this embodiment, the top end face of the lower support plate 31 is concave, concentric with the spherical tank 1 and attached to the bottom of the spherical tank 1. The distance between the plane containing the upper edge of the lower support plate 31 and the bottom of the spherical tank 1 is 1 / 5 of the radius of the spherical tank.

[0034] In this embodiment, a pair of hinge seats 35 are provided on the bottom end face of the lower support plate 31 and the outer wall of the base 32. The pair of hinge seats 35 are connected by a spring 36. The hinge seats 35 provided on the bottom end face of the lower support plate 31 are connected to the tensioning assembly 4.

[0035] In this embodiment, the tensioning component 4 includes a buckle 41 and an elastic band 42. The elastic band 42 is connected to the buckle 41 at both ends, and the buckle 41 is connected to the upper energy-absorbing component 2 and the lower energy-absorbing component 3 respectively.

[0036] In the installation process of this invention, the base 32 of the lower energy-absorbing component 3 is first fixed to the structural base plate of the aircraft, and the upper energy-absorbing component 2 is fixed to the structural top plate of the aircraft through the hinge seat 23. Then, the spherical tank 1 is installed on the lower support plate 31 of the lower energy-absorbing component 3. After it is installed in close contact with the lower support plate 31, the upper support plate 21 of the upper energy-absorbing component 2 is also installed in close contact with the top of the spherical tank 1. After the installation is completed, the buckles 41 at both ends of the elastic band 42 are connected to the hinge seat 23 on the upper end face of the upper support plate 21 and the hinge seat 35 on the lower end face of the lower support plate 31, respectively, to tighten the spherical tank 1 and complete the installation of the entire device.

[0037] When the aircraft encounters turbulence or other situations during flight that could cause the spherical tank 1 to collide, the upper energy-absorbing component 2 controls the vertical extension and retraction of the hinge 23 through the ring 25 and spring 24. The tensioning component 4 tightens the spherical tank 1 between the upper energy-absorbing component 2 and the lower energy-absorbing component 3. The relative piston movement between the cylinder 34 at the bottom of the lower support plate 31 and the base 32 in the lower energy-absorbing component 3 restricts the movement of the spherical tank 1 to the axial direction of the base 32 in the lower energy-absorbing component 3, thus preventing a crash and ensuring the safety of the spherical tank 1.

Claims

1. A drop-resistant container structure, comprising a spherical tank, characterized in that: The top of the spherical tank is provided with an upper energy-absorbing component, and the bottom is provided with a lower energy-absorbing component. The top of the upper energy-absorbing component is connected to the top plate of the aircraft structure, and the bottom of the lower energy-absorbing component is connected to the bottom plate of the aircraft structure. Multiple tensioning components that position and tighten the spherical tank are connected between the upper energy-absorbing component and the lower energy-absorbing component. The upper energy-absorbing assembly includes an upper support plate, hinges, hinge base 1, spring 1, and a ring. The bottom of the upper support plate is attached to the top of the spherical tank. Multiple circumferentially distributed hinge base 1 are fixed to the top of the upper support plate. Hinges are connected to the multiple circumferentially distributed hinge base 1. The top of the hinges is connected to the hinge base 1 fixed to the top plate of the aircraft structure. The middle of the multiple hinges is connected to the same ring through the spring 1. The lower energy-absorbing component includes a lower support plate, a base, and flexible energy-absorbing material. The base is a cylindrical structure and is fixed to the structural base plate of the aircraft. The lower support plate is set on the base and its top is connected to the spherical tank. The flexible energy-absorbing material is filled inside the base. The bottom of the lower support plate is provided with a cylinder, which extends into the base and is gap-fitted with the base and the flexible energy-absorbing material. When vibrating, the cylinder moves up and down along the base like a piston.

2. The impact-resistant container structure according to claim 1, characterized in that: The upper support plate has a ring-shaped structure. The area of ​​the top of the spherical tank covered by the upper support plate is between 0 and 1 / 4 of the top area of ​​the spherical tank. The distance between the plane containing the lower edge of the upper support plate and the top of the spherical tank is between 0 and 1 / 3 of the radius of the spherical tank.

3. The impact-resistant container structure according to claim 1, characterized in that: The upper support plate, the ring, and the spherical tank are concentric.

4. The impact-resistant container structure according to claim 1, characterized in that: The top end face of the lower support plate is concave, concentric with the spherical tank and in contact with the bottom of the spherical tank. The distance between the plane containing the upper edge of the lower support plate and the bottom of the spherical tank is between 0 and 1 / 4 of the radius of the spherical tank.

5. The impact-resistant container structure according to claim 1, characterized in that: The bottom end face of the lower support plate and the outer wall of the base are provided with a pair of hinge seats, and the two hinge seats are connected by a spring.

6. The impact-resistant container structure according to claim 1, characterized in that: The hinge seat 2 provided on the bottom end face of the lower support plate is connected to the tensioning assembly.

7. The impact-resistant container structure according to claim 1, characterized in that: The tensioning assembly includes a buckle and an elastic band. The elastic band has buckles at both ends, and the buckles are connected to the upper energy-absorbing assembly and the lower energy-absorbing assembly, respectively.

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