Wing body butt joint quick-release mechanism

Abstract

The utility model discloses a wing body butt joint quick release mechanism which comprises an upper plate piece, a lower plate piece, a plug pin assembly and a pair of limiting assemblies. The upper plate piece and the lower plate piece are connected through a plate piece connecting piece, and sliding ways are formed in the upper plate piece and the lower plate piece; one end of the bolt assembly is located in the slide way, and the bolt assembly slides in the slide way, so that opening and closing operation of the wing body butt joint quick-release mechanism can be achieved, and shearing force and bending moment transmitted by the wing body butt joint lug piece are transmitted to the fuselage butt joint lug piece; the limiting assemblies are located on the two sides of the plug pin assembly. According to the utility model, tools are not needed, quick disassembly and assembly can be realized, the opening and closing operations can be completed by pushing and pulling the corresponding bolt assemblies and the limiting assemblies by hands, tools are not needed, the quick disassembly and assembly function can be realized, and the use requirements are met; the wing body butt joint quick release device well solves the technical problem of butt joint quick release of wing bodies of large unmanned aerial vehicles, and has the advantages of being free of tools, quick to disassemble and assemble, anti-vibration and high in reliability.

Description

Technical Field

[0001] The utility model belongs to the technical field of mechanical engineering, and in particular relates to a wing-body docking quick-release mechanism. Background Art

[0002] With the extensive application of drones on modern battlefields, the number of drones used by troops has increased significantly. Traditional drone components are mostly connected with bolts and nuts, and disassembly and assembly require tools and are slow, which can no longer meet the requirements of rapid disassembly and installation on the battlefield. A few drones with small payloads and take-off weights use quick-release pins, but their reliability is low and their anti-vibration ability is weak, making them unsuitable for large drones.

[0003] Therefore, in order to solve the above technical problems, it is necessary to provide a wing-body docking quick-release mechanism.

[0004] The information disclosed in this background technology section is only intended to increase the understanding of the overall background of the present invention, and should not be regarded as an admission or any form of suggestion that the information constitutes the prior art already known to those skilled in the art. Utility Model Content

[0005] The purpose of the utility model is to provide a wing-body docking and quick-disconnection mechanism, which can solve the technical problem of difficult wing-body docking and quick-disconnection of large-scale unmanned aerial vehicles.

[0006] In order to achieve the above-mentioned purpose, the technical solution provided by a specific embodiment of the present invention is as follows:

[0007] A wing-body docking quick-release mechanism comprises an upper plate, a lower plate, a latch assembly and a pair of limit assemblies;

[0008] The upper plate and the lower plate are connected by a plate connecting member, and slideways are provided on both the upper plate and the lower plate;

[0009] One end of the latch assembly is located inside the slideway, and the latch assembly slides inside the slideway to realize the opening and closing operations of the wing-body docking quick release mechanism, and transmits the shear force and bending moment from the wing-body docking lug to the fuselage docking lug;

[0010] A pair of limiting assemblies are located on both sides of the latch assembly and are used to limit the latch assembly in a closed state.

[0011] In one or more embodiments of the present invention, the latch assembly includes a push-pull rod, a load-bearing pin, and a first bolt. The load-bearing pin is plugged into the wing-body docking lug. The load-bearing pin is provided with an assembly hole that matches the push-pull rod, and the bottom end of the push-pull rod is plugged into the assembly hole.

[0012] The push-pull rod is provided with a screw hole matching the first bolt, and the first bolt is screwed inside the screw hole to fix the push-pull rod.

[0013] In one or more embodiments of the present invention, the push-pull rod is an aluminum alloy piece, machined from a pre-stretched aluminum sheet, and anodized on the surface;

[0014] The bearing pin is made of steel, which is made of high-strength stainless steel rod, then subjected to heat treatment after rough processing, and then fine-processed and shaped, and the surface is passivated;

[0015] The first bolt is a hexagon socket head bolt.

[0016] In one or more embodiments of the present invention, the limiting assembly includes a limiting pull rod, a spring, and a second bolt. The upper plate and the lower plate are provided with openings matching the limiting pull rod, and the limiting pull rod is slidably connected inside the opening.

[0017] The spring is fixedly mounted on one end of the limiting pull rod, and the other end of the spring is fixed by a second bolt.

[0018] In one or more embodiments of the present invention, the limit rod is an aluminum alloy part, which is machine-formed using a pre-stretched aluminum plate and anodized on the surface;

[0019] The spring is made of steel, wound with high-strength spring steel wire, and its surface is phosphated;

[0020] The second bolt is a hexagon socket round head bolt, and the size of the spring limit fixing force can be adjusted by changing the length of the second bolt.

[0021] In one or more embodiments of the present invention, the upper plate and the lower plate are both aluminum alloy parts, which are machined using pre-stretched aluminum plates and anodized on the surface;

[0022] The plate connecting piece is any one of a hexagon socket head bolt, a countersunk bolt or a hexagon socket head bolt.

[0023] In one or more embodiments of the present invention, the upper panel is covered with an organism skin, and the organism skin is fixed to the upper panel via a panel mounting member.

[0024] In one or more embodiments of the present invention, the panel mounting member is any one of a countersunk rivet or a countersunk bolt, and is fixed to the fuselage skin by riveting or screwing.

[0025] Compared with the existing technology, the utility model does not require tools and can be quickly disassembled and assembled. The opening and closing operations can be completed by manually pushing and pulling the corresponding latch components and limit components. No tools are required, and the rapid disassembly and assembly function can be achieved to meet the use needs.

[0026] The utility model is anti-vibration and has high reliability. The load-bearing pin is made of high-strength stainless steel bar, which is heat-treated after rough processing and then fine-processed into shape. It can withstand high shear force and bending moment. The use of stainless steel and passivation treatment makes it have excellent corrosion resistance.

[0027] The utility model solves the technical difficulties of quick-disassembly of the wing body of a large UAV well, and has the advantages of no need for tools, quick disassembly and assembly, anti-vibration and high reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0029] Figure 1 This is a structural diagram of a wing-body docking quick-release mechanism in one embodiment of the present invention (the fuselage skin is not shown);

[0030] Figure 2 This is a structural diagram of a wing-body docking quick-release mechanism in one embodiment of the present invention (showing the fuselage skin);

[0031] Figure 3 This is a side view of a wing-body docking quick-release mechanism in one embodiment of the present utility model;

[0032] Figure 4 This is an exploded view of a wing-body docking quick-release mechanism in one embodiment of the present utility model;

[0033] Figure 5 This is a partial disassembly diagram of a wing-body docking quick-release mechanism in one embodiment of the present utility model.

[0034] Description of main reference numerals:

[0035] 10. Latch assembly; 11. Push-pull rod; 12. Load-bearing pin; 13. First bolt; 20. Limit assembly; 21. Limit pull rod; 22. Spring; 23. Second bolt; 30. Upper plate; 40. Lower plate; 50. Plate connector; 60. Plate mounting part; 70. Wing-body docking ear; 80. Fuselage skin. DETAILED DESCRIPTION

[0036] In order to enable those skilled in the art to better understand the technical solutions of the present invention, the following will be combined with the drawings of the embodiments of the present invention to clearly and completely describe the technical solutions of the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of the present invention.

[0037] like Figure 1-Figure 5 As shown, a wing-body docking quick-release mechanism in one embodiment of the present invention includes a latch assembly 10, a pair of stopper assemblies 20, an upper plate 30, and a lower plate 40. The upper plate 30 and lower plate 40 are connected by a plate connector 50, which is used to mount the latch assembly 10 and the stopper assemblies 20 and provide space for their fixed or sliding movement. Both the upper plate 30 and the lower plate 40 are aluminum alloy parts, machined from pre-stretched aluminum sheets, and anodized on the surface.

[0038] Preferably, the plate connector 50 is any one of a hexagon socket head bolt, a countersunk bolt or a hexagon head bolt, and standard parts can be selected.

[0039] like Figure 4 As shown, slideways are provided on the upper plate 30 and the lower plate 40, and one end of the latch assembly 10 is located inside the slideway. The latch assembly 10 slides inside the slideway to realize the opening and closing operations of the wing-fuselage docking quick-release mechanism, and transmits the shear force and bending moment transmitted from the wing-fuselage docking ear 70 to the fuselage docking ear.

[0040] Specifically, such as Figure 4 and Figure 5 As shown, the latch assembly 10 includes a push-pull rod 11, a bearing pin 12, and a first bolt 13. The push-pull rod 11 is an aluminum alloy, machined from pre-stretched aluminum sheet and anodized. The bearing pin 12 is a steel component, constructed from high-strength stainless steel rods that undergo rough machining, heat treatment, and fine machining, with a passivated surface. The first bolt 13 is a hexagon socket head bolt.

[0041] The load-bearing pin 12 is inserted into the wing-body docking lug 70. The load-bearing pin 12 has an assembly hole that matches the push-pull rod 11. The bottom end of the push-pull rod 11 is inserted into the assembly hole. The push-pull rod 11 has a screw hole that matches the first bolt 13. The first bolt 13 is screwed into the screw hole to fix the push-pull rod 11. The top end of the push-pull rod 11 is inserted into the slide. By driving the push-pull rod 11 to slide inside the slide, the wing-body docking quick-release mechanism can be opened and closed.

[0042] A pair of limiting assemblies 20 are located on both sides of the latch assembly 10 and are used to limit the latch assembly 10 in the closed state to prevent it from moving.

[0043] Specifically, such as Figure 4 and Figure 5 As shown, the limiter assembly 20 includes a limiter rod 21, a spring 22, and a second bolt 23. The limiter rod 21 is an aluminum alloy part, machine-formed from pre-stretched aluminum sheet and anodized. The spring 22 is a steel part, wound with high-strength spring steel wire and phosphated. The second bolt 23 is a standard hexagon socket head bolt. The length of the second bolt 23 can be adjusted to adjust the limiter force of the spring 22.

[0044] The upper plate 30 and the lower plate 40 have openings that match the limit rod 21. The limit rod 21 is slidably connected within the openings. The push-pull rod 11 also has a slot that matches the limit rod 21. By engaging the limit rod 21 within the slot, the push-pull rod 11 is fixed in position. A spring 22 is fixedly mounted on one end of the limit rod 21, and the other end of the spring 22 is fixed in position by a second bolt 23.

[0045] The upper panel 30 is covered with an organism skin 80 , and the organism skin 80 is fixed to the upper panel 30 via a panel mounting member 60 .

[0046] Preferably, the plate mounting member 60 is any one of a countersunk rivet or a countersunk bolt, and a standard part can be selected and fixed to the fuselage skin 80 by riveting or screwing.

[0047] Working principle:

[0048] First, the latch assembly 10 , a pair of limit assemblies 20 , the upper plate 30 , the lower plate 40 and the plate connector 50 are combined into an integral structure, and then the upper plate 30 is fixed to the fuselage skin 80 through the plate mounting member 60 .

[0049] When in the open state, pulling the limit rod 21 can compress the spring 22 in the limit assembly 20, so that the limit rod 21 avoids the movement path of the latch assembly 10, and pushing the push-pull rod 11 in the latch assembly 10 can insert the load-bearing pin 12 into the wing-body docking ear piece 70. When the limit rod 21 is released, it rebounds under the action of the compressed spring 22 and enters the card slot of the push-pull rod 11, preventing the latch assembly 10 from loosening during the flight of the aircraft, and the wing-body docking quick-release mechanism is turned into the closed state;

[0050] When in the closed state, pulling the limit rod 21 can compress the spring 22 in the limit assembly 20, so that the limit rod 21 avoids the movement path of the latch assembly 10. Pulling the push-pull rod 11 in the latch assembly 10 can pull the load-bearing pin 12 out of the wing-body docking ear 70. Release the limit rod 21, and it will rebound under the action of the compressed spring 22, and the wing-body docking quick-release mechanism will become open.

[0051] Compared with the existing technology, the utility model does not require tools and can be quickly disassembled and assembled. The opening and closing operations can be completed by manually pushing and pulling the corresponding latch components and limit components. No tools are required, and the rapid disassembly and assembly function can be achieved to meet the use needs.

[0052] The utility model is anti-vibration and has high reliability. The load-bearing pin is made of high-strength stainless steel bar, which is heat-treated after rough processing and then fine-processed into shape. It can withstand high shear force and bending moment. The use of stainless steel and passivation treatment makes it have excellent corrosion resistance.

[0053] The utility model solves the technical difficulties of quick-disassembly of the wing body of a large UAV well, and has the advantages of no need for tools, quick disassembly and assembly, anti-vibration and high reliability.

[0054] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the present invention is defined by the appended claims, not the foregoing description, and all variations within the meaning and range of equivalents of the claims are intended to be encompassed within the present invention. Any reference sign in a claim should not be construed as limiting the claim to which it relates.

[0055] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

Claims

1. A wing-body docking quick-release mechanism, characterized in that: include: Upper plate parts; The upper plate and the lower plate are connected by a plate connecting member, and the upper plate and the lower plate are both provided with a slideway; A latch assembly, one end of which is located inside the slideway. The latch assembly slides inside the slideway to open and close the wing-body docking quick-release mechanism, and transmits the shear force and bending moment from the wing-body docking tab to the fuselage docking tab. A pair of limiting components are located on both sides of the latch component and are used to limit the latch component in a closed state.

2. The wing-body docking quick-release mechanism according to claim 1, characterized in that: The latch assembly includes a push-pull rod, a load-bearing pin and a first bolt. The load-bearing pin is plugged into the wing-body docking lug. The load-bearing pin is provided with an assembly hole that matches the push-pull rod. The bottom end of the push-pull rod is plugged into the assembly hole. The push-pull rod is provided with a screw hole matching the first bolt, and the first bolt is screwed inside the screw hole to fix the push-pull rod.

3. The wing-body docking quick-release mechanism according to claim 2, characterized in that: The push-pull rod is made of aluminum alloy; The load-bearing pin is a steel part; The first bolt is a hexagon socket head bolt.

4. The wing-body docking quick-release mechanism according to claim 1, characterized in that: The limiting assembly includes a limiting rod, a spring and a second bolt. The upper plate and the lower plate are provided with openings matching the limiting rod, and the limiting rod is slidably connected inside the openings. The spring is fixedly mounted on one end of the limiting pull rod, and the other end of the spring is fixed by a second bolt.

5. The wing-body docking quick-release mechanism according to claim 4, characterized in that: The limit pull rod is made of aluminum alloy; The spring is made of steel; The second bolt is a hexagon socket round head bolt, and the size of the spring limit fixing force can be adjusted by changing the length of the second bolt.

6. The wing-fuselage docking quick-release mechanism according to claim 1, characterized in that: The upper plate and the lower plate are both aluminum alloy parts; The plate connecting piece is any one of a hexagon socket head bolt, a countersunk bolt or a hexagon head bolt.

7. The wing-body docking quick-release mechanism according to claim 1, characterized in that: The upper plate is covered with an organism skin, and the organism skin is fixed to the upper plate via a plate mounting member.

8. The wing-body docking quick-release mechanism according to claim 7, characterized in that: The plate mounting piece is any one of a countersunk rivet or a countersunk bolt, and is fixed to the fuselage skin by riveting or screwing.

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