Wing body butt joint quick release mechanism and manufacturing method thereof

Abstract

The invention discloses a wing body butt joint quick release mechanism which comprises an upper plate, a lower plate, 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. Compared with the prior art, tools are not needed, quick disassembly and assembly can be achieved, opening and closing operation can be completed only by pushing and pulling the corresponding plug pin assemblies and the limiting assemblies by hands, the tools are not needed, the quick disassembly and assembly function can be achieved, and the use requirement is met; according to the invention, the technical difficulty of butt joint and quick disassembly of the wing body of the large unmanned aerial vehicle is well solved, and the device has the advantages of no need of tools, quick disassembly and assembly, anti-vibration and high reliability.

Description

Technical Field

[0001] The invention belongs to the technical field of mechanical engineering, and in particular relates to a wing-body docking quick-release mechanism and a manufacturing method thereof. 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 view of the above technical problems, it is necessary to provide a wing-fuselage docking quick-release mechanism and a manufacturing method thereof.

[0004] The information disclosed in this background technology section is only intended to enhance the understanding of the overall background of the invention and should not be regarded as an acknowledgment or any form of suggestion that the information constitutes the prior art already known to a person skilled in the art. Summary of the invention

[0005] The object of the present invention is to provide a wing-body docking quick-release mechanism and a manufacturing method thereof, which can solve the technical problem of difficult wing-body docking quick-release of large unmanned aerial vehicles.

[0006] In order to achieve the above object, a 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 via a plate connecting member, and slideways are provided on 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 ear piece to the fuselage docking ear piece;

[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 ear piece, the load-bearing pin is provided with an assembly hole matching 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 using a pre-stretched aluminum plate, and anodized on the surface;

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

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

[0016] In one or more embodiments of the present invention, the limit assembly includes a limit rod, a spring and a second bolt, the upper plate and the lower plate are provided with openings matching the limit rod, and the limit 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 pull 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 a steel part, wound with high-strength spring steel wire, and the 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 head 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 by 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] In one or more embodiments of the present invention, a method for manufacturing a wing-body docking quick-release mechanism comprises the following steps:

[0026] S1. Parts Manufacturing

[0027] S2. Mechanism assembly

[0028] S2.1. Insert the push-pull rod into the assembly hole on the load-bearing pin and fix it with the first bolt to form a latch assembly, and place the latch assembly into the slideway on the lower plate;

[0029] S2.2. Dip the end of the spring into thread locking glue and install it into the prefabricated threaded hole of the limit pull rod, and then put it into the opening on the lower plate;

[0030] S2.3. Fasten the upper plate, connect the upper plate and the lower plate with the plate connector, screw the second bolt into the threaded hole at the spring to block the spring, and adjust the spring limit fixing force by changing the length of the second bolt;

[0031] S3. Mechanism Installation

[0032] S3.1. Use the wing-body docking lugs and fuselage skin to test fit and position, drill connection holes on the fuselage skin and countersink the sockets, and use plate mounting parts to fix them to the fuselage skin by riveting or screwing.

[0033] In one or more embodiments of the present invention, in S1, the specific steps of part manufacturing include:

[0034] S1.1. Use a pre-stretched aluminum plate machine to process the push-pull rod, limit pull rod, upper plate and lower plate in sequence, and perform anodizing treatment on their surfaces;

[0035] S1.2, use high-strength stainless steel bars to perform rough processing, heat treatment, and then fine processing to obtain load-bearing pins, and passivate the surface;

[0036] S1.3. Use high-strength spring steel wire to wind the spring and perform phosphating treatment on its surface.

[0037] Compared with the prior art, the present invention 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 quick disassembly and assembly function can be achieved to meet the use requirements.

[0038] The invention is vibration-proof and highly reliable. The load-bearing pin is made of high-strength stainless steel bars, which are heat-treated after rough processing and then finely processed to form. It can withstand high shear force and bending moment. Stainless steel and passivation treatment are used to make it have excellent anti-corrosion performance.

[0039] The invention solves the technical difficulties of quick-disassembly and docking of the wing body of a large unmanned aerial vehicle, and has the advantages of no need for tools, quick assembly and disassembly, anti-vibration and high reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. 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 creative work.

[0041] 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);

[0042] 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);

[0043] Figure 3 It is a side view of a wing-body docking quick-release mechanism in one embodiment of the present invention;

[0044] Figure 4 An exploded view of a wing-body docking quick-release mechanism in one embodiment of the present invention;

[0045] Figure 5 The present invention is a partial disassembly diagram of a wing-body docking quick-release mechanism in one embodiment of the present invention.

[0046] Description of main reference numerals:

[0047] 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 member; 70. Wing-body docking ear; 80. Fuselage skin. DETAILED DESCRIPTION

[0048] In order to enable those skilled in the art to better understand the technical solutions in the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments 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 creative work should fall within the scope of protection of the present invention.

[0049] like Figure 1-Figure 5As shown, a wing-body docking quick-release mechanism in one embodiment of the present invention comprises a latch assembly 10, a pair of stopper assemblies 20, an upper plate 30 and a lower plate 40. The upper plate 30 and the lower plate 40 are connected by a plate connector 50, which is used to install the latch assembly 10 and the stopper assemblies 20 and provide space for their fixation or sliding. The upper plate 30 and the lower plate 40 are both aluminum alloy parts, which are machined and formed using pre-stretched aluminum plates, and the surfaces are anodized.

[0050] Preferably, the plate connector 50 is any one of a hexagon socket head bolt, a countersunk bolt or a hexagon socket head bolt, and standard parts can be selected.

[0051] 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-furrature docking quick-release mechanism, and transmits the shear force and bending moment transmitted from the wing-furrature docking ear 70 to the fuselage docking ear.

[0052] Specifically, 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, wherein the push-pull rod 11 is an aluminum alloy part, which is machined using a pre-stretched aluminum plate and anodized on the surface. The bearing pin 12 is a steel part, which is made of a high-strength stainless steel bar, subjected to rough machining, heat treatment, and then fine machining and passivation on the surface. The first bolt 13 is a hexagon socket head bolt.

[0053] The load-bearing pin 12 is inserted into the wing-body docking ear piece 70, and an assembly hole matching the push-pull rod 11 is provided on the load-bearing pin 12. The bottom end of the push-pull rod 11 is inserted into the assembly hole, and a screw hole matching the first bolt 13 is provided on the push-pull rod 11. 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 slideway, and the opening and closing operations of the wing-body docking quick release mechanism can be realized by driving the push-pull rod 11 to slide inside the slideway.

[0054] 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 a closed state to prevent it from moving.

[0055] Specifically, Figure 4 and Figure 5 As shown, the limit assembly 20 includes a limit rod 21, a spring 22 and a second bolt 23, wherein the limit rod 21 is an aluminum alloy part, which is machine-formed using a pre-stretched aluminum plate and anodized on the surface. The spring 22 is a steel part, which is wound using high-strength spring steel wire and phosphated on the surface. The second bolt 23 is a standard part of a hexagon socket round head bolt, and the size of the limit fixing force of the spring 22 can be adjusted by changing the length of the second bolt 23.

[0056] The upper plate 30 and the lower plate 40 are provided with openings matching the limit rod 21, and the limit rod 21 is slidably connected inside the openings. The push-pull rod 11 is also provided with a slot matching the limit rod 21, and the limit rod 21 is connected inside the slot to achieve the limit fixation of the push-pull rod 11. The spring 22 is fixedly mounted on one end of the limit rod 21, and the other end of the spring 22 is fixed by a second bolt 23.

[0057] The upper panel 30 is covered with a body skin 80 , and the body skin 80 is fixed to the upper panel 30 via a panel mounting member 60 .

[0058] 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.

[0059] A method for manufacturing a wing-body docking quick-release mechanism comprises the following steps:

[0060] S1. Parts Manufacturing

[0061] S1.1, using a pre-stretched aluminum plate machine to sequentially process the push-pull rod 11, the limit pull rod 21, the upper plate 30 and the lower plate 40, and anodize their surfaces;

[0062] S1.2, high-strength stainless steel bars are rough-processed, heat-treated, and fine-processed to obtain the bearing pins 12, and the surfaces thereof are passivated;

[0063] S1.3. Use high-strength spring steel wire to wind the spring 22, and perform phosphating treatment on its surface.

[0064] S2. Mechanism assembly

[0065] S2.1. Insert the push-pull rod 11 into the assembly hole on the load-bearing pin 12 and connect and fix it with the first bolt 13 to form a latch assembly 10. Put the latch assembly 10 into the slideway on the lower plate 40.

[0066] S2.2, dip the end of the spring 22 into thread locking glue and install it into the prefabricated threaded hole of the limit rod 21, and then put it into the opening of the lower plate 40;

[0067] S2.3. Close the upper plate 30, connect the upper plate 30 and the lower plate 40 using the plate connector 50, and then screw the second bolt 23 into the threaded hole at the spring 22 to block the spring 22, and adjust the limit fixing force of the spring 22 by changing the length of the second bolt 23;

[0068] S3. Mechanism Installation

[0069] S3.1. Use the wing-body docking lugs 70 and the fuselage skin 80 to test fit and position, drill connection holes on the fuselage skin 80 and countersink the holes, and use the plate mounting parts 60 to fix them to the fuselage skin 80 by riveting or screwing.

[0070] Working principle:

[0071] First, the latch assembly 10 , a pair of limit assemblies 20 , the upper panel 30 , the lower panel 40 and the panel connector 50 are combined into an integral structure, and then the upper panel 30 is fixed to the fuselage skin 80 by the panel mounting member 60 .

[0072] 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, and releasing the limit rod 21, which 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 becomes closed;

[0073] 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 piece 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.

[0074] Compared with the prior art, the present invention 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 quick disassembly and assembly function can be achieved to meet the use requirements.

[0075] The invention is vibration-proof and highly reliable. The load-bearing pin is made of high-strength stainless steel bars, which are heat-treated after rough processing and then finely processed to form. It can withstand high shear force and bending moment. Stainless steel and passivation treatment are used to make it have excellent anti-corrosion performance.

[0076] The invention solves the technical difficulties of quick-disassembly and docking of the wing body of a large unmanned aerial vehicle, and has the advantages of no need for tools, quick assembly and disassembly, anti-vibration and high reliability.

[0077] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0078] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description 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 may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A wing-body docking quick-release mechanism, It is characterized in that include: Upper plate parts; A lower plate, wherein the upper plate and the lower plate are connected via a plate connecting member, and slideways are provided on the upper plate and the lower plate; A latch assembly, one end of which 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 ear piece to the fuselage docking ear piece; A pair of limiting components, the pair of limiting components are located on both sides of the latch assembly and are used to limit the latch assembly in a closed state.

2. A wing-body docking quick-release mechanism according to claim 1, It is 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 ear piece, the load-bearing pin is provided with an assembly hole matching the push-pull rod, and 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. A wing-body docking quick-release mechanism according to claim 2, It is characterized in that The push-pull rod is an aluminum alloy part, which is machined using a pre-stretched aluminum plate and anodized on the surface; The bearing pin is a steel part, which is made of high-strength stainless steel rod, subjected to heat treatment after rough processing, and then finely processed and shaped, and the surface is passivated; The first bolt is a hexagon socket round head bolt.

4. A wing-body docking quick-release mechanism according to claim 1, It is characterized in that 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; 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. A wing-body docking quick-release mechanism according to claim 4, It is characterized in that The limit pull rod is an aluminum alloy part, which is machine-formed using a pre-stretched aluminum plate and anodized on the surface; The spring is a steel part, wound with high-strength spring steel wire, and the surface is phosphated; 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. A wing-body docking quick-release mechanism according to claim 1, It is characterized in that 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; The plate connecting piece is any one of a hexagon socket head bolt, a countersunk head bolt or a hexagon socket head bolt.

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

8. A wing-body docking quick-release mechanism according to claim 7, It is 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.

9. A method for manufacturing a wing-body docking quick-release mechanism, It is characterized in that The following steps are involved: S1. Parts Manufacturing S2. Mechanism assembly S2.

1. Insert the push-pull rod into the assembly hole on the load-bearing pin and fix it with the first bolt to form a latch assembly, and place the latch assembly into the slideway on the lower plate; S2.

2. Dip the end of the spring into thread locking glue and install it into the prefabricated threaded hole of the limit pull rod, and then put it into the opening on the lower plate; S2.

3. Fasten the upper plate, connect the upper plate and the lower plate with the plate connector, screw the second bolt into the threaded hole at the spring to block the spring, and adjust the spring limit fixing force by changing the length of the second bolt; S3. Mechanism Installation S3.

1. Use the wing-body docking lugs and fuselage skin to test fit and position, drill connection holes on the fuselage skin and countersink the sockets, and use plate mounting parts to fix them to the fuselage skin by riveting or screwing.

10. A method for manufacturing a wing-body docking quick-release mechanism according to claim 9, It is characterized in that In S1, the specific steps of parts manufacturing include: S1.

1. Use a pre-stretched aluminum plate machine to process the push-pull rod, limit pull rod, upper plate and lower plate in sequence, and perform anodizing treatment on their surfaces; S1.2, use high-strength stainless steel bars to perform rough processing, heat treatment, and then fine processing to obtain load-bearing pins, and passivate the surface; S1.

3. Use high-strength spring steel wire to wind the spring and perform phosphating treatment on its surface.

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