CN218949471U

CN218949471U - Integrated aircraft shell

Info

Publication number: CN218949471U
Application number: CN202223316317.5U
Authority: CN
Inventors: 余新峰; 康成博
Original assignee: Xiamen Yunlun Intelligent Technology Co ltd
Current assignee: Xiamen Yunlun Intelligent Technology Co ltd
Priority date: 2022-12-09
Filing date: 2022-12-09
Publication date: 2023-05-02
Anticipated expiration: 2032-12-09

Abstract

The utility model provides an integrated aircraft shell which comprises a second composite material layer body, a third composite material layer body, a partition frame and a top frame, wherein the edges of the third composite material layer body and the second composite material layer body are fixedly connected through the partition frame and the top frame, and the third composite material layer body and the second composite material layer body are stacked up and down; at least one conductive sheet is also clamped between the third composite material layer body and the second composite material layer body. The utility model can assemble and integrally arrange the conductive sheet (aluminum sheet) and the cable with the machine body shell, thereby not only improving the strength of the machine body shell and greatly improving the durability of the circuit, but also ensuring that the cable is easy and convenient to run and safer, and simultaneously improving the assembling speed and being beneficial to use; by winding the copper wire with the insulating layer and the two ends of the conductive sheet (aluminum sheet) to one circle, the resistance of the conductive sheet (aluminum sheet) is kept uniform after the conductive sheet (aluminum sheet) is electrified, and the safety is improved.

Description

Integrated aircraft shell

Technical Field

The utility model relates to an aircraft shell, in particular to an integrated aircraft shell.

Background

An aircraft includes a series of devices such as a drone or a drone. Existing aircraft typically include an outer shell and various electronic components mounted within the outer shell, with electrical connections made between the various electronic components through wires or flat cables. This approach has the following drawbacks: the wire or the flat cable is exposed in the shell, is easy to damage and even break in the operation processes of disassembly, maintenance and the like, and leads to the failure of normal operation of the aircraft. In addition, the wires or the flat cables occupy the internal installation space of the shell, so that the layout, disassembly, assembly, heat dissipation and the like of other electronic devices are affected; when the number of wires or flat cables is large, the wires are easy to disorder, and inconvenience is brought to disassembly and maintenance. In addition, the existing shell is usually made of plastic and the like, has poor strength and is easy to damage.

Disclosure of Invention

The present utility model provides an integrated aircraft housing that effectively solves the above-mentioned problems.

The utility model is realized in the following way:

an integrated aircraft shell comprises a second composite material layer body, a third composite material layer body, a bulkhead and a top frame,

the edges of the third composite material layer body and the second composite material layer body are fixedly connected with each other through a separation frame and a top frame, and the third composite material layer body and the second composite material layer body are stacked up and down;

at least one conductive sheet is also clamped between the third composite material layer body and the second composite material layer body; and copper wires with insulating layers, which ensure the uniformity of resistance, are wound at two ends of the conducting strip, and exposed conducting contacts are formed.

As a further improvement, the bottom surface of the second composite material layer body is also fixedly provided with the first composite material layer body.

As a further improvement, the end surfaces of the third composite material layer body and the second composite material layer body are respectively provided with a caulking groove for clamping the top frame.

As a further improvement, one end of the top frame is rotatably provided with a special-shaped abutting plate, and a special-shaped groove matched with the special-shaped abutting plate is formed in the embedded groove of the third composite material layer body.

As a further improvement, the top frame is fixedly connected with two mounting blocks, and two sides of the special-shaped butt plate are rotatably arranged between the two mounting blocks through shaft rods and are provided with torsion coil springs which enable the special-shaped butt plate to rotate towards the inside of the special-shaped groove.

As a further improvement, the special-shaped butt plate is also fixedly provided with a plurality of upper clamping bulges, and the special-shaped groove is provided with a plurality of upper butt grooves for being matched with the upper clamping bulges.

As a further improvement, the inner parts of the upper arc edge and the lower arc edge of the bulkhead are fixedly connected with a first filling layer and a second filling layer respectively, and a plurality of reinforcing ribs are fixedly connected between the first filling layer and the second filling layer.

As a further improvement, the first filling layer and the second filling layer are made of rubber materials and are used for improving the strength of the bulkhead.

As a further improvement, the first composite material layer body and the second composite material layer body are made of glass fiber materials, and the third composite material layer body is made of glass fiber reinforced plastic materials.

As a further improvement, the bulkhead is fixedly connected with a plurality of panels at the position of abutting against the third composite material layer body; the two sides of the front end surface of the panel are integrally provided with protruding parts, and the outer side surfaces of the protruding parts are provided with a plurality of clamping grooves; the third composite material layer body is provided with side grooves for placing a plurality of transverse plates on two sides of each conducting strip, the front end face of each transverse plate is fixedly connected with a transverse protruding plate which is in plug-in fit with the clamping grooves, and one end of each transverse protruding plate extends out of each side groove;

a reserved seam for installing the panel is reserved between the third composite material layer body and the conducting strip.

The beneficial effects of the utility model are as follows:

(1) The conductive sheet (aluminum sheet) and the machine body shell are integrally arranged, so that the strength of the machine shell is ensured, the forming degree of the machine shell is improved, and the machine shell is equivalent to a circuit board, so that the durability of a circuit is greatly improved, and meanwhile, the aluminum sheet is lighter in texture and lower in construction and transportation cost; after the cable can be integrally installed with the engine body shell, the wiring is simpler and more convenient, the assembly is also quicker, and after the engine body shell made of carbon fiber is broken, the elastic modulus of the cable is smaller than that of metal copper in the cable, so that the cable can not be broken under the condition that the damage amount of the cable is larger than that of the engine body shell, and the cable can be formed into a whole with the engine body shell more safely.

(2) Through winding the both ends of taking insulating layer copper wire and conducting strip (aluminum sheet) to the round, the resistance keeps even after making conducting strip (aluminum sheet) circular telegram, prevents directly to take insulating layer copper wire spot welding on the aluminum sheet, causes the uneven and blowing of power line resistance of great electric current, improves the security.

(3) Through setting up of caulking groove and top frame isotructure, can be better with engine body shell and other casings looks equipment concatenation, guarantee the fastness between engine body shell and the other casings, make it can not become flexible, simultaneously, after accomplishing with both concatenation, other connecting pieces such as rethread current screw fix, engine body shell can not slide between other casings, improves the leakproofness, other connecting pieces such as also the staff's installation screw of being convenient for are comparatively swift simple and convenient.

(4) By setting the mechanisms such as the bulkhead, the strength of the bulkhead can be better improved, the bulkhead is prevented from being broken, the bearing strength is improved, the strength of the bulkhead is improved, the strength of the machine shell can be improved, and the forming degree is better.

(5) Through the setting of structures such as the bulkhead and the side groove, the bulkhead and the engine body shell can be better spliced and installed, and meanwhile, the conducting strip can be safely fixed on the third composite material layer body, so that the conducting strip is prevented from loosening, and the follow-up use is facilitated.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some examples of the present utility model and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 is a front view of the present utility model.

Fig. 2 is an exploded view of the present utility model.

Fig. 3 is a right side view of the present utility model.

Fig. 4 is a top view of the panel of the present utility model.

Figure 5 is a cross-sectional view of a former of the present utility model.

FIG. 6 is a schematic structural diagram of a third composite layer and a top frame according to the present utility model.

FIG. 7 is a schematic view of a portion of a third composite layer according to the present utility model.

Fig. 8 is an enlarged view of the present utility model a.

Fig. 9 is a schematic diagram of a winding structure of the conductive sheet of the present utility model.

Reference numerals illustrate:

1. a first composite layer; 2. a second composite layer; 3. a third composite layer; 4. a spacer frame; 5. a conductive sheet; 6. a panel; 7. a groove; 8. a top frame; 9. a clamping groove; 10. a first filler layer; 11. a second filler layer; 12. reinforcing ribs; 13. a special-shaped groove; 14. an upper butt joint groove; 15. a mounting block; 16. a shaft lever; 17. a torsion coil spring; 18. a special-shaped butt plate; 19. an upper clamping bulge; 20. reserving a seam; 21. a side groove; 22. a cross plate; 23. and a transverse protruding plate.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments. All other embodiments, based on the embodiments of the utility model, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the utility model. Thus, the following detailed description of the embodiments of the utility model, as presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, based on the embodiments of the utility model, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the utility model.

In the description of the present utility model, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present utility model, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.

Referring to fig. 1-8, an integrated aircraft shell comprises a second composite layer 2, a third composite layer 3, a former 4 and a top frame 8. Specifically, the second composite material layer body 2, the third composite material layer body 3 and the first composite material layer body 1 are at least provided with three groups, and the three groups of the second composite material layer body 2, the third composite material layer body 3 and the first composite material layer body 1 include, but are not limited to, three groups, four groups or a plurality of groups, and a proper number is selected according to actual requirements.

The edges of the third composite material layer body 3 and the second composite material layer body 2 are fixedly connected with each other through the separation frame 4 and the top frame 8, and the third composite material layer body 3 and the second composite material layer body 2 are stacked up and down.

At least one conducting strip 5 is also clamped between the third composite material layer body 3 and the second composite material layer body 2; copper wires with insulating layers (refer to figure 9) which ensure uniform resistance are wound at the two ends of the conducting strip 5, exposed conducting contacts are formed, and meanwhile, the two ends of the conducting strip 5 can ensure uniform resistance through welding similar circuit board sockets.

Preferably, the conductive sheet 5 is an aluminum sheet. The shell is preferably carbon fiber and other materials with better conductivity, and when in production and manufacture, the aluminum sheet and the shell are preferably manufactured into an integrated fitting in a pouring mode and the like, so that the strength of the shell is enhanced, the later assembly difficulty of equipment is reduced, the forming degree of the aluminum sheet and the shell is better, meanwhile, glass fiber reinforced plastic can be selected to replace an original insulating layer, and the affinity of the aluminum sheet and the glass fiber reinforced plastic of an epoxy resin material is higher, so that the strength is higher. The aluminum sheet and the shell are integrally arranged, so that the shell is equivalent to a circuit board, and the durability of the circuit is greatly improved.

Specifically, as another embodiment of the present utility model, the conductive sheet 5 may be made of a conductive material such as a general-purpose cable, copper, or carbon fiber sheet. The cables are routed and arranged through a specific U-shaped groove (not shown in the figure), so that the cables can be orderly fixed in the interlayer of the shell, the strength of the shell can be improved, the cables cannot shake in the shell, the assembly step is simplified, the shape of the cables is not limited, and the proper cables are selected according to the use requirement.

The copper wire with the insulating layer is wound at the two ends of the conducting strip 5 in a spot welding mode, after the conducting strip 5 and the copper wire with the insulating layer are wound, the conducting strip is bonded with the third composite material layer body 3, and the resistance of the copper wire with the insulating layer wound to one circle can be kept uniform after the aluminum sheet is electrified, so that the copper wire with the insulating layer is prevented from being directly spot welded on the aluminum sheet, and the uneven and burning of the power line resistance with larger current is avoided, and the safety is improved.

The bottom surface of the second composite material layer body 2 is also provided with the first composite material layer body 1 in an adhesive or integral forming manner.

The end surfaces of the third composite material layer body 3 and the second composite material layer body 2 are provided with caulking grooves 7 for clamping the top frame 8.

The top frame 8 is rotatably provided with a special-shaped abutting plate 18 at one end, a special-shaped groove 13 matched with the special-shaped abutting plate 18 is arranged in the embedded groove 7 of the third composite material layer body 3, the top frame 8 is fixedly connected with two mounting blocks 15, two sides of the special-shaped abutting plate 18 are rotatably arranged between the two mounting blocks 15 through a shaft rod 16, and a torsion coil spring 17 which enables the special-shaped abutting plate 18 to rotate towards the inside of the special-shaped groove 13 is arranged. Specifically, the torsion coil spring 17 is socket-fitted to the outer wall of the shaft 16, and both ends of the torsion coil spring 17 are respectively connected to the mounting block 15 and the profiled abutment plate 18, so that the profiled abutment plate 18 can be rotated and rebounded by the torsion coil spring 17. The special-shaped butt plate 18 is also fixedly provided with a plurality of upper clamping bulges 19. Specifically, the upper clamping protrusion 19 and the special-shaped abutment plate 18 are provided by welding or integral molding. The profiled groove 13 is provided with a number of upper abutment grooves 14 for cooperation with upper clamping projections 19. Specifically, the inner diameter of the upper docking slot 14 is slightly larger than the outer diameter of the upper snap-in protrusion 19.

When the caulking groove 7 and the top frame 8 are assembled, the special-shaped butt plate 18 can be turned over inwards by the torsion coil spring 17, after the turning over is completed, the caulking groove 7 and the top frame 8 are spliced, the special-shaped butt plate 18 is rebounded towards the direction of the special-shaped groove 13 by utilizing the elasticity of the torsion coil spring 17, and then the structures such as the special-shaped butt plate 18 and the special-shaped groove 13 are mutually clamped, a hooking seam (not shown in the drawing) is reserved between the caulking groove 7 and the top frame 8 after the caulking groove 7 and the top frame 8 are spliced, an iron hook (with smaller thickness) can be inserted into the hooking seam generated by the splicing of the caulking groove 7 and the top frame 8, the iron hook can be hooked with the special-shaped butt plate 18, the special-shaped butt plate 18 and the special-shaped groove 13 are completely clamped, the firmness of the caulking groove 7 and the top frame 8 is ensured, and finally, the connecting parts such as screws in the prior art are used for fixing again, and the secondary fixing effect is better, so that the shell formed by the first composite material layer body 1, the second composite material layer body 2, the third composite material layer body 3 and the conductive sheet 5 are convenient to connect with other shells, and the shell bodies are not easy to loose.

The inner parts of the upper arc edge and the lower arc edge of the bulkhead 4 are fixedly connected with a first filling layer 10 and a second filling layer 11 respectively. Specifically, the first filling layer 10 and the second filling layer 11 are adhered and fixed inside the bulkhead 4. And a plurality of reinforcing ribs 12 are fixedly connected between the first filling layer 10 and the second filling layer 11. Specifically, the reinforcing ribs 12 are bonded and fixed to the first filler layer 10 and the second filler layer 11. The reinforcing ribs 12 are made of nylon, so that the strength of the bulkhead 4 is improved, the bulkhead 4 can improve the strength of a machine body, and the forming degree is better.

The first filling layer 10 and the second filling layer 11 are made of rubber material for improving the strength of the bulkhead 4.

The first composite material layer body 1 and the second composite material layer body 2 are made of glass fiber materials, and the third composite material layer body 3 is made of glass fiber reinforced plastic materials. Specifically, the first composite material layer 1, the second composite material layer 2 and the third composite material layer 3 may be made of kevlar layers, carbon fiber layers (carbon fiber is a good conductor and has high conductivity), and appropriate material layers may be added according to practical requirements, and the layer attached to the conductive sheet 5 is an insulating layer.

The former 4 is fixedly connected with a plurality of panels 6 at the location of the butt joint of the third composite material layer 3. In particular, the panel 6 is connected to the former 4 by means of welding; the two sides of the front end surface of the panel 6 are provided with protruding parts in an integrated manner, and the outer side surfaces of the protruding parts are provided with a plurality of clamping grooves 9; the third composite material layer body 3 is provided with side grooves 21 for placing a plurality of transverse plates 22 on two sides of each conducting strip 5, the front end faces of the transverse plates 22 are fixedly connected with transverse protruding plates 23 which are in plug-in fit with the clamping grooves 9, and one ends of the transverse protruding plates 23 extend out of the side grooves 21. Specifically, the lateral protruding plate 23 and the lateral plate 22 are provided by welding or integral molding;

a reserved seam 20 for installing the panel 6 is reserved between the third composite material layer body 3 and the conductive sheet 5. A reserved seam 20 (not shown) is reserved between the five groups of conducting strips 5 and the third composite material layer body 3.

The working principle of the utility model is as follows:

the conductive sheet 5 is adhered and installed between the first composite material layer body 1, the second composite material layer body 2 and the third composite material layer body 3 to form a whole, namely a shell of a machine body, then the bulkhead 4 can be inserted into the reserved joint 20 by utilizing the panels 6, the clamping grooves 9 on the convex parts of the groups of panels 6 are just matched and clamped with the transverse convex plates 23 on the transverse plates 22, the concave parts of the panels 6 are also matched with the conductive sheet 5, and then the conductive sheet 5 can be clamped and fixed, so that the bulkhead 4 can be combined and spliced into a whole with the first composite material layer body 1, the second composite material layer body 2, the third composite material layer body 3 and the conductive sheet 5, and the integrated arrangement not only can ensure the strength of the whole shell, but also can design the shell into a circuit board, thereby greatly improving the durability of a circuit; the conducting strips 5 can also be replaced by cables, and the cables can be orderly arranged between the shell structures through special setting, so that the strength of the shell can be enhanced, and the cables are simpler and more convenient to wire and more rapid to assemble.

The above description is only of the preferred embodiments of the present utility model and is not intended to limit the present utility model, and various modifications and variations may be made to the present utility model by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.

Claims

1. The integrated aircraft shell comprises a second composite material layer body (2), a third composite material layer body (3), a bulkhead (4) and a top frame (8), and is characterized in that,

the edges of the third composite material layer body (3) and the second composite material layer body (2) are fixedly connected with each other through a partition frame (4) and a top frame (8), and the third composite material layer body (3) and the second composite material layer body (2) are stacked up and down;

at least one conducting strip (5) is also clamped between the third composite material layer body (3) and the second composite material layer body (2); copper wires with insulating layers, which ensure the uniformity of resistance, are wound at the two ends of the conducting strip (5) and form exposed conducting contacts.

2. The integrated aircraft shell according to claim 1, wherein the bottom surface of the second composite layer (2) is further provided with a first composite layer (1).

3. The integrated aircraft shell according to claim 1, wherein the end faces of the third composite layer body (3) and the second composite layer body (2) are provided with caulking grooves (7) for clamping the top frame (8).

4. An integrated aircraft shell according to claim 3, wherein one end of the top frame (8) is rotatably provided with a profiled abutment plate (18), and the inside of the caulking groove (7) of the third composite material layer body (3) is provided with a profiled groove (13) adapted to the profiled abutment plate (18).

5. The integrated aircraft shell according to claim 4, wherein the top frame (8) is fixedly connected with two mounting blocks (15), two sides of the special-shaped butt plate (18) are rotatably arranged between the two mounting blocks (15) through a shaft lever (16), and a torsion coil spring (17) for enabling the special-shaped butt plate (18) to rotate towards the inside of the special-shaped groove (13) is arranged.

6. The integrated aircraft shell according to claim 4 or 5, wherein the profiled abutment plate (18) is further provided with a plurality of upper clamping projections (19), and the profiled groove (13) is provided with a plurality of upper abutment grooves (14) for engaging the upper clamping projections (19).

7. The integrated aircraft shell according to claim 1, wherein a first filling layer (10) and a second filling layer (11) are fixedly connected to the inner parts of the upper arc edge and the lower arc edge of the bulkhead (4), and a plurality of reinforcing ribs (12) are fixedly connected between the first filling layer (10) and the second filling layer (11).

8. The integrated aircraft shell according to claim 7, wherein the first and second filling layers (10, 11) are made of rubber for improving the strength of the bulkhead (4).

9. The integrated aircraft shell according to claim 2, wherein the first composite material layer (1) and the second composite material layer (2) are both made of glass fiber materials, and the third composite material layer (3) is made of glass fiber reinforced plastics materials.

10. The integrated aircraft shell according to claim 1, wherein the bulkhead (4) is fixedly connected with a number of panels (6) at the location of the butt joint of the third composite layer (3); the two sides of the front end surface of the panel (6) are integrally provided with protruding parts, and the outer side surfaces of the protruding parts are provided with a plurality of clamping grooves (9); the third composite material layer body (3) is provided with side grooves (21) for placing a plurality of transverse plates (22) on two sides of each conducting strip (5), the front end surface of each transverse plate (22) is fixedly connected with a transverse protruding plate (23) which is in plug-in fit with the clamping groove (9), and one end of each transverse protruding plate (23) extends out of the side groove (21);

a reserved seam (20) for installing the panel (6) is reserved between the third composite material layer body (3) and the conducting strip (5).