Blended wing body quick release mechanism and manufacturing method thereof

Abstract

The application discloses a wing-body butt joint quick-release mechanism, which comprises an upper plate, a lower plate, a latch assembly and a pair of limiting assemblies; the upper plate and the lower plate are connected through a plate connecting piece; the upper plate and the lower plate are both provided with a slide; one end of the latch assembly is located inside the slide; the latch assembly slides in the slide to realize the opening and closing operation of the wing-body butt joint quick-release mechanism, and the shear force and the bending moment from the wing-body butt joint ear piece are transmitted to the fuselage butt joint ear piece; the pair of limiting assemblies are located on the two sides of the latch assembly. Compared with the prior art, the wing-body butt joint quick-release mechanism can be quickly disassembled without tools, and the opening and closing operation can be completed by only pushing and pulling the corresponding latch assembly and limiting assembly by hand, so that the quick disassembly function is realized, the use requirement is met, the technical difficulty of the wing-body butt joint quick-release of the large unmanned aerial vehicle is solved, and the wing-body butt joint quick-release mechanism has the advantages of tool-free, quick disassembly, anti-vibration, high reliability and the like.

Description

Technical Field

[0001] This invention belongs to the field of mechanical engineering technology, specifically relating to a wing-body docking quick-release mechanism and its manufacturing method. Background Technology

[0002] With the widespread use of drones on the modern battlefield, the number of drones used by the military has increased significantly. Traditional drone components are mostly connected by bolts and nuts, which require tools for disassembly and assembly and are slow, and can no longer meet the requirements of rapid disassembly and assembly on the battlefield. A few drones with small payloads and low takeoff weight use quick-release pins, but they have low reliability and weak anti-vibration and detachment capabilities, and are not suitable for large drones.

[0003] Therefore, in order to address the above-mentioned technical problems, it is necessary to provide a wing-body docking quick-release mechanism and its manufacturing method.

[0004] The information disclosed in this background section is intended only to enhance the understanding of the overall background of the invention and should not be construed as an admission or in any way implying that the information constitutes prior art known to those skilled in the art. Summary of the Invention

[0005] The purpose of this invention is to provide a wing-body docking quick-release mechanism and its manufacturing method, which can solve the technical problem of difficult wing-body docking quick release for large UAVs.

[0006] To achieve the above objectives, a specific embodiment of the present invention provides the following technical solution:

[0007] A wing-body docking quick-release mechanism includes an upper plate, a lower plate, a pin assembly, and a pair of limiting assemblies;

[0008] The upper plate and the lower plate are connected by a plate connector, and both the upper plate and the lower plate are provided with slide rails;

[0009] One end of the pin assembly is located inside the slide rail. By sliding the pin assembly inside the slide rail, the opening and closing operations of the wing-body docking quick-release mechanism can be realized, and the shear force and bending moment transmitted from the wing-body docking lugs can be transmitted to the fuselage docking lugs.

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

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

[0012] The push-pull rod has a screw hole that matches the first bolt. The first bolt is screwed into 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 part, which is machined from a pre-stretched aluminum plate and anodized.

[0014] The load-bearing pin is a steel part, which is rough machined from high-strength stainless steel bars, heat-treated, and then precision machined and passivated.

[0015] The first bolt is an internal hexagon head bolt.

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

[0017] The spring is fixedly installed at one end of the limiting rod, and the other end of the spring is limited and fixed by a second bolt.

[0018] In one or more embodiments of the present invention, the limiting rod is an aluminum alloy part, which is formed by machining a pre-stretched aluminum plate and anodized.

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

[0020] The second bolt is an internal hexagon head bolt, and the spring limiting and fixing force can be adjusted by changing the length of the second bolt.

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

[0022] The plate connector is any one of an internal hexagon head bolt, a countersunk head bolt, or an external hexagon head bolt.

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

[0024] In one or more embodiments of the present invention, the plate mounting component is any one of countersunk rivets or countersunk bolts, and is fixed to the body 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 includes 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 bearing pin and fix it with the first bolt to assemble the pin assembly. Place the pin assembly into the slide rail on the lower plate.

[0029] S2.2. Dip the end of the spring in thread-locking adhesive and insert it into the pre-made threaded hole of the limit rod, and then put it into the opening on the lower plate.

[0030] S2.3. Fasten the upper plate, use the plate connector to connect the upper plate and the lower plate, then 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. Trial fitting and positioning are carried out using wing-body docking lugs and fuselage skin. Connecting holes are drilled on the fuselage skin and countersunk holes are made. Plate mounting parts are used to fix the parts to the fuselage skin by riveting or screwing.

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

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

[0035] S1.2. After rough machining of high-strength stainless steel bars, heat treatment is performed, followed by precision machining to obtain load-bearing pins, and their surfaces are passivated.

[0036] S1.3. Use high-strength spring steel wire to wind the spring and phosphate its surface.

[0037] Compared with the prior art, the present invention requires no tools and can be quickly disassembled and assembled. The opening and closing operations can be completed by simply pushing and pulling the corresponding pin components and limit components by hand. No tools are needed, and the quick disassembly and assembly function can be achieved to meet the needs of use.

[0038] This invention features vibration-proof and high reliability. The load-bearing pin is made of high-strength stainless steel bar, which is rough-machined, heat-treated, and then precision-machined. It can withstand high shear force and bending moment. The use of stainless steel and passivation treatment results in excellent corrosion resistance.

[0039] This invention effectively solves the technical difficulties of quick detachment of wing-body docking for large UAVs, and has the advantages of tool-free operation, rapid assembly and disassembly, vibration-proof design, and high reliability. Attached Figure Description

[0040] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0041] Figure 1 This is a structural diagram of a wing-body docking quick-release mechanism according to an embodiment of the present invention (airframe skin is not shown);

[0042] Figure 2 This is a structural diagram of a wing-body docking quick-release mechanism according to an embodiment of the present invention (showing the fuselage skin);

[0043] Figure 3 This is a side view of a wing-body docking quick-release mechanism according to an embodiment of the present invention;

[0044] Figure 4 This is an exploded view of a wing-body docking quick-release mechanism according to an embodiment of the present invention;

[0045] Figure 5 This is a partial disassembly diagram of a wing-body docking quick-release mechanism according to an embodiment of the present invention.

[0046] Explanation of key figure labels:

[0047] 10. Pin assembly; 11. Push-pull rod; 12. Load-bearing pin; 13. First bolt; 20. Limiting assembly; 21. Limiting rod; 22. Spring; 23. Second bolt; 30. Upper plate; 40. Lower plate; 50. Plate connector; 60. Plate mounting piece; 70. Wing-body docking lug; 80. Fuselage skin. Detailed Implementation

[0048] To enable those skilled in the art to better understand the technical solutions of this invention, the technical solutions of the embodiments of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this invention, and not all embodiments. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of this invention.

[0049] like Figures 1-5As shown, a quick-release mechanism for wing-body docking in one embodiment of the present invention includes a pin assembly 10, a pair of limiting 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 pin assembly 10 and the limiting assemblies 20 and to provide space for their fixing or sliding. Both the upper plate 30 and the lower plate 40 are aluminum alloy parts, machined from pre-stretched aluminum plates, and anodized.

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

[0051] like Figure 4 As shown, both the upper plate 30 and the lower plate 40 are provided with slides. One end of the pin assembly 10 is located inside the slide. By sliding the pin assembly 10 inside the slide, the opening and closing operation of the wing-body docking quick-release mechanism can be realized, and the shear force and bending moment transmitted from the wing-body docking lug 70 can be transmitted to the fuselage docking lug.

[0052] Specifically, such as Figure 4 and Figure 5 As shown, the pin assembly 10 includes a push-pull rod 11, a load-bearing pin 12, and a first bolt 13. The push-pull rod 11 is an aluminum alloy part, machined from pre-stretched aluminum plate and anodized. The load-bearing pin 12 is a steel part, roughly machined from high-strength stainless steel bar, heat-treated, and then precision-machined and passivated. The first bolt 13 is a hexagonal head bolt.

[0053] The load-bearing pin 12 is inserted into the wing-body docking lug 70. The load-bearing pin 12 has a mounting hole that matches the push-pull rod 11. The bottom end of the push-pull rod 11 is inserted into the mounting 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 rail. By driving the push-pull rod 11 to slide within the slide rail, the opening and closing operations of the wing-body docking quick-release mechanism can be achieved.

[0054] A pair of limiting components 20 are located on both sides of the pin assembly 10 to limit the pin assembly 10 in the closed state and prevent it from moving.

[0055] Specifically, such as Figure 4 and Figure 5 As shown, the limiting assembly 20 includes a limiting rod 21, a spring 22, and a second bolt 23. The limiting rod 21 is an aluminum alloy part, machined from pre-stretched aluminum plate, 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 hexagonal head bolt, and the limiting and 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 have openings that match the limiting rod 21. The limiting rod 21 is slidably connected inside the openings. The push-pull rod 11 also has a slot that matches the limiting rod 21. By engaging the limiting rod 21 inside the slot, the push-pull rod 11 is limited and fixed. The spring 22 is fixedly installed at one end of the limiting rod 21, and the other end of the spring 22 is limited and fixed by the second bolt 23.

[0057] An organic body skin 80 is covered on the upper plate 30, and the organic body skin 80 is fixed to the upper plate 30 by the plate mounting part 60.

[0058] Preferably, the plate mounting component 60 is either a countersunk rivet or a countersunk bolt, and standard parts can be selected. It is fixed to the body skin 80 by riveting or screwing.

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

[0060] S1, Parts Manufacturing

[0061] S1.1. The push-pull rod 11, the limit rod 21, the upper plate 30 and the lower plate 40 are processed in sequence using a pre-stretched aluminum plate machine, and their surfaces are anodized.

[0062] S1.2. After rough machining of high-strength stainless steel bars, heat treatment is performed, followed by precision machining to obtain load-bearing pin 12, and its surface is passivated.

[0063] S1.3 Spring 22 is made by winding high-strength spring steel wire and its surface is phosphated.

[0064] S2, Mechanism Assembly

[0065] S2.1 Insert the push-pull rod 11 into the assembly hole on the bearing pin 12 and connect and fix it with the first bolt 13 to assemble the pin assembly 10. Place the pin assembly 10 into the slide rail on the lower plate 40.

[0066] S2.2. Dip the end of the spring 22 in thread-locking adhesive and insert it into the pre-made threaded hole of the limit rod 21, and then put it into the opening on the lower plate 40.

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

[0068] S3, Mechanism Installation

[0069] S3.1. Trial fitting and positioning are performed using the wing-body docking lugs 70 and the fuselage skin 80. Connecting holes are drilled on the fuselage skin 80 and countersunk holes are made. The plate mounting parts 60 are fixed to the fuselage skin 80 by riveting or screwing.

[0070] Working principle:

[0071] The overall structure is first composed of a pin assembly 10, a pair of limit assemblies 20, an upper plate 30, a lower plate 40, and a plate connector 50. Then, the upper plate 30 is fixed to the body skin 80 by the plate mounting piece 60.

[0072] When in the open state, pulling the limit lever 21 compresses the spring 22 in the limit assembly 20, causing the limit lever 21 to avoid the movement path of the pin assembly 10. Pushing the push-pull rod 11 in the pin assembly 10 allows the load-bearing pin 12 to be inserted into the wing-body docking lug 70. Releasing the limit lever 21 causes it to spring back under the action of the compressed spring 22 and enter the slot of the push-pull rod 11, preventing the pin assembly 10 from loosening during aircraft flight. The wing-body docking quick-release mechanism then becomes the closed state.

[0073] When in the closed state, pulling the limit lever 21 compresses the spring 22 in the limit assembly 20, causing the limit lever 21 to avoid the movement path of the pin assembly 10. Pulling the push-pull lever 11 in the pin assembly 10 pulls the load-bearing pin 12 out of the wing-body docking lug 70. Releasing the limit lever 21 causes it to spring back under the action of the compressed spring 22, and the wing-body docking quick-release mechanism becomes open.

[0074] Compared with the prior art, the present invention requires no tools and can be quickly disassembled and assembled. The opening and closing operations can be completed by simply pushing and pulling the corresponding pin components and limit components by hand. No tools are needed, and the quick disassembly and assembly function can be achieved to meet the needs of use.

[0075] This invention features vibration-proof and high reliability. The load-bearing pin is made of high-strength stainless steel bar, which is rough-machined, heat-treated, and then precision-machined. It can withstand high shear force and bending moment. The use of stainless steel and passivation treatment results in excellent corrosion resistance.

[0076] This invention effectively solves the technical difficulties of quick detachment of wing-body docking for large UAVs, and has the advantages of tool-free operation, rapid assembly and disassembly, vibration-proof design, and high reliability.

[0077] 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 invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0078] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A wing-body docking quick-release mechanism, characterized in that, include: Upper plate parts; The lower plate is connected to the upper plate via a plate connector, and both the upper and lower plates are provided with slide tracks. The pin assembly has one end located inside the slide rail. By sliding the pin assembly inside the slide rail, the opening and closing operations of the wing-body docking quick-release mechanism can be realized, and the shear force and bending moment transmitted from the wing-body docking lugs can be transmitted to the fuselage docking lugs. The pin assembly includes a push-pull rod, a load-bearing pin, and a first bolt. The load-bearing pin is inserted into the fuselage docking lug. The load-bearing pin has an assembly hole that matches the push-pull rod. The bottom end of the push-pull rod is inserted into the assembly hole. The push-pull rod has a screw hole that matches the first bolt. The first bolt is screwed into the screw hole to fix the push-pull rod. The push-pull rod is an aluminum alloy part, machined from pre-stretched aluminum plate, and anodized on the surface. The load-bearing pin is a steel part, which is rough machined from high-strength stainless steel bars, heat-treated, and then precision machined and passivated. The first bolt is an internal hexagon head bolt; A pair of limiting components, the pair of limiting components being located on both sides of the latch assembly, for limiting the latch assembly in the closed state; The limiting assembly includes a limiting rod, a spring, and a second bolt. The upper and lower plates have openings that match the limiting rod, and the limiting rod is slidably connected inside the openings. The spring is fixedly installed at one end of the limiting rod, and the other end of the spring is fixed by a second bolt. The limiting rod is an aluminum alloy part, which is machined using pre-stretched aluminum plate and anodized. The spring is made of steel, wound with high-strength spring steel wire, and phosphated on the surface; The second bolt is an internal hexagon head bolt, and the spring limiting and fixing force can be adjusted by changing the length of the second bolt.

2. The wing-body docking quick-release mechanism according to claim 1, characterized in that, Both the upper and lower plates are aluminum alloy parts, machined from pre-stretched aluminum plates, and anodized on the surface. The plate connector is any one of an internal hexagon head bolt, a countersunk head bolt, or an external hexagon head bolt.

3. The wing-body docking quick-release mechanism according to claim 1, characterized in that, The upper plate is covered with an organic skin, which is fixed to the upper plate by a plate mounting component.

4. The wing-body docking quick-release mechanism according to claim 3, characterized in that, The plate mounting component is either a countersunk rivet or a countersunk bolt, and is fixed to the body skin by riveting or screwing.

5. A method for manufacturing a wing-body docking quick-release mechanism as described in any one of claims 1-4, characterized in that, Includes the following steps: S1, Parts Manufacturing S2, Mechanism Assembly S2.1 Insert the push-pull rod into the assembly hole on the bearing pin and fix it with the first bolt to assemble the pin assembly. Place the pin assembly into the slide rail on the lower plate. S2.

2. Dip the end of the spring in thread-locking adhesive and insert it into the pre-made threaded hole of the limit rod, and then put it into the opening on the lower plate. S2.

3. Fasten the upper plate, use the plate connector to connect the upper plate and the lower plate, then 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. Trial fitting and positioning are carried out using wing-body docking lugs and fuselage skin. Connecting holes are drilled on the fuselage skin and countersunk holes are made. Plate mounting parts are used to fix the parts to the fuselage skin by riveting or screwing.

6. A method for manufacturing a wing-body docking quick-release mechanism according to claim 5, characterized in that, In step S1, the specific steps for manufacturing the part include: S1.

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

2. After rough machining of high-strength stainless steel bars, heat treatment is performed, followed by precision machining to obtain load-bearing pins, and their surfaces are passivated. S1.

3. Use high-strength spring steel wire to wind the spring and phosphate its surface.

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