Machine head connecting structure capable of being quickly disassembled and assembled without tool

Abstract

The invention discloses a machine head connecting structure capable of being rapidly disassembled and assembled without a tool, and belongs to the field of unmanned aerial vehicle body structures. Comprising a nose adapter frame and a fuselage frame front end edge strip, one end of the nose adapter frame is coaxially embedded into the open end of the nose cover skin and fixedly connected with the nose cover skin, and the other end of the nose adapter frame is coaxially embedded into the fuselage frame front end edge strip and detachably connected with the fuselage frame front end edge strip in a butt joint mode. A plurality of first limiting bosses are arranged at the end, embedded into the front end edge strip of the machine body frame, of the machine head switching frame, a plurality of second limiting bosses are correspondingly arranged at the end, facing the machine head switching frame, of the front end edge strip of the machine body frame, grooves are formed beside the first limiting bosses, protruding blocks are arranged beside the second limiting bosses, and the grooves and the protruding blocks are provided with pin holes respectively. When the machine head adapting frame and the machine body frame front end edge strip are in butt joint in place, the protruding block is located in the groove and inserted into the pin hole through the quick-release pin to be fixed, and the second limiting boss axially limits the first limiting boss. According to the connecting structure provided by the invention, the problem that the nose cover skin and the fuselage frame front end edge strip are inconvenient to disassemble and assemble in the prior art is solved.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicle (UAV) body structures, and in particular to a head connection structure that can be quickly disassembled and assembled without tools. Background Art

[0002] The nose cover of most drones is a non-load-bearing structure. The non-load-bearing nose cover only includes a shell-shaped nose cover skin. The nose cover skin maintains the shape of the drone's nose and has a rectifying effect. Its internal space will accommodate part of the drone's mission payload (the mission payload is supported and installed through the drone's fuselage frame). In order to facilitate the maintenance and replacement of the mission payload, the nose cover needs to be quickly disassembled and assembled. The existing nose cover skin installation method is: the open end of the nose cover skin is sleeved on the outer periphery of the front edge strip of the fuselage frame, and then the nose cover skin and the fuselage frame are fixedly connected by multiple fastening components evenly distributed along a circle, so that the nose cover skin and the fuselage skin profile wrapped outside the fuselage frame are butted against each other. The fastening components used to fix the nose cover skin and the front edge strip of the fuselage frame are generally standard parts such as a support nut + bolt combination, or a screw + rivet nut combination. The disassembly and assembly of such standard parts mostly require tools, which is time-consuming and labor-intensive. Excessive disassembly and assembly will cause the standard part mounting holes to deform, and there are risks of standard parts being lost or mis-assembled during the disassembly and assembly process.

[0003] Therefore, it is necessary to provide a tool-free quick disassembly and assembly head connection structure to solve the above problems. Summary of the Invention

[0004] Technical issues to be solved: To overcome the shortcomings of the prior art, the present invention provides a tool-free, quick-disassembly nose connection structure. By designing a nose adapter frame, one end of the adapter frame is fixedly connected to the open end of the nose cowl skin, while the other end removably fits into the front edge strip of the fuselage frame. The matching design of the nose adapter frame and the front edge strip of the fuselage frame at the fitting point enables tool-free assembly and disassembly of the two, thus resolving the inconvenient assembly and disassembly problem of the nose cowl skin and the front edge strip of the fuselage frame in the prior art.

[0005] The technical solution of the present invention is: a nose connection structure that can be quickly disassembled without tools, comprising: a nose adapter frame and a front end edge strip of the fuselage frame; the nose adapter frame is annular, one end of which is coaxially embedded in the open end of the nose cover skin and fixedly connected to the edge of the open end of the nose cover skin, and the other end of which is coaxially embedded in the front end edge strip of the fuselage frame and can be detachably connected thereto; Among them, the nose adapter frame is embedded in the radial outer surface of one end of the front end edge strip of the fuselage frame, and a plurality of first limiting bosses are evenly distributed along a circle. A radially inwardly concave groove is provided between two adjacent first limiting bosses, and a first pin hole is provided at the center of the bottom of the groove; a plurality of second limiting bosses are evenly distributed around the radial inner surface of the front end edge strip of the fuselage frame toward one end of the nose adapter frame, and the second limiting bosses correspond to the first limiting bosses one by one. A radially inwardly convex block is provided between two adjacent second limiting bosses, and a second pin hole is provided in the middle of the block along the radial direction; When the head adapter frame and the front end edge strip of the fuselage frame are docked in place, the protrusion is located in the groove, the first pin hole and the second pin hole are coaxial and fixed by quick-release pins, the first limiting boss is located on the inner side of the second limiting boss, and the second limiting boss forms an axial limit on the first limiting boss.

[0006] A further technical solution of the present invention is: the length, width and protrusion height of the first limiting boss and the second limiting boss are the same, and when the nose adapter frame and the front end edge strip of the fuselage frame are docked into place, the first limiting boss and the second limiting boss are aligned along the heading.

[0007] A further technical solution of the present invention is that when the first limiting boss and the second limiting boss are butt-jointed with the front end edge strip of the nose adapter frame and the fuselage frame, there is a gap of 0.5mm-1mm between the two.

[0008] A further technical solution of the present invention is: the top of the groove and one end facing the front edge of the fuselage frame are open, and are used to dock with the protrusion; the groove width is greater than the width of the protrusion, and is used to ensure that when the first limiting boss is misaligned with the second limiting boss, the protrusion can fall into the groove, and when the first limiting boss and the second limiting boss are aligned along the heading, the second pin hole of the protrusion and the first pin hole of the groove are coaxial.

[0009] A further technical solution of the present invention is: a positioning column is provided next to the groove of the head adapter frame, and the positioning column is fixed on the outer diameter surface of the head adapter frame along the radial direction, and a positioning groove is provided next to the protrusion of the front end edge strip of the fuselage frame, and the positions of the positioning groove and the positioning column correspond to each other; when the head adapter frame and the front end edge strip of the fuselage frame are docked, the positioning column is inserted into the positioning groove, and the positioning groove and the positioning column cooperate to limit the angular position of the head adapter frame and the front end edge strip of the fuselage frame when docking.

[0010] A further technical solution of the present invention is: the positioning groove is a T-shaped hollow structure, including an entrance section and a groove section, the entrance section faces the positioning column, the entrance section is used to position and dock with the positioning column, the groove section is arranged along the circumferential arc surface of the front end edge strip of the fuselage frame, the groove section is used for the positioning column to slide in the groove, and the two ends of the groove section form sliding limit limits for the positioning column.

[0011] A further technical solution of the present invention is that the nose adapter frame is fixed to the edge of the opening end of the nose cover skin by gluing or screwing.

[0012] A drone adopts the tool-free quick-disassembly and assembly nose connection structure, wherein the front end edge strip of the body frame is completely embedded in the fuselage skin, and the front end of the fuselage skin is provided with a third pin hole and a positioning slot hole, wherein the third pin hole and the second pin hole are coaxial and have the same size, and the positioning slot hole and the positioning slot have the same structure and are coaxial.

[0013] A method for quick disassembly and assembly of the nose and fuselage of the UAV without tools, wherein the nose adapter frame is installed at the opening end of the nose cover skin, and the front edge strip of the fuselage frame is installed in the fuselage skin. The method includes: During installation, align the positioning post with the entrance section of the positioning slot and push the nose cover toward the fuselage. When the positioning post enters the groove section of the positioning slot, rotate the nose cover so that the positioning post slides to the end of the groove section close to the protruding end. At this time, insert the quick-release pin from the outside to the inside in sequence into the third pin hole, the second pin hole, and the first pin hole to lock the connection between the nose and the fuselage. During disassembly, remove the quick-release pin, rotate the nose cover skin in the opposite direction, and slide the positioning column to the intersection of the groove section and the entrance section. At this time, pull the nose cover skin outward to make the nose adapter frame detach from the front edge strip of the fuselage frame, completing the separation and disassembly of the nose and fuselage.

[0014] The beneficial effects of the present invention are as follows: The present invention provides a tool-free, quick-disassembly nose connection structure. By designing a nose adapter frame, the nose adapter frame is matched with an improved fuselage frame front end edge strip structure. One end of the nose adapter frame is fixedly connected to the inner wall surface of the open end of the nose cowl skin, a non-load-bearing structure, while the other end of the nose adapter frame is embedded in the fuselage frame front end edge strip and mated therewith. This structure integrates the nose adapter frame and the nose cowl skin as a whole, enabling tool-free, quick-disassembly and assembly with the fuselage frame front end edge strip.

[0015] The present invention has a plurality of first limiting bosses evenly distributed around the radial outer surface of the nose adapter frame away from the nose cover skin, and a plurality of second limiting bosses evenly distributed around the radial inner surface of the fuselage frame front end edge strip toward the nose adapter frame. The second limiting bosses correspond to the first limiting bosses one-to-one and have the same size. When the nose adapter frame and the fuselage frame front end edge strip are docked, the first limiting bosses and the second limiting bosses are first misaligned and plugged in. Then, by rotating the nose adapter frame, the two corresponding limiting bosses are aligned along the heading direction, that is, the axial direction of the nose adapter frame, so that the first limiting boss is located inside the second limiting boss, forming an axial limit to prevent the nose adapter frame from falling out. When disassembling, the second limiting boss is rotated in the opposite direction to release the axial limit of the first limiting boss.

[0016] The structure of the present invention cooperates with the groove of the nose adapter frame and the protrusion of the front end edge strip of the fuselage frame, and passes through the corresponding pin holes on the groove and the protrusion through the quick-release pin, thereby preventing the nose adapter frame and the front end edge strip of the fuselage frame from rotating relative to each other, and can further limit the axial direction to prevent the nose adapter frame from falling out of the front end edge strip of the fuselage frame.

[0017] The present invention, through the coordinated arrangement of the positioning post and the positioning groove, plays a role in preventing misalignment between the nose adapter frame and the front edge strip of the fuselage frame, and can also play a role in limiting the nose adapter frame when it is installed and rotated relative to the front edge strip of the fuselage frame. The groove section in the positioning groove defines the rotation limit position of the positioning post, so that when the positioning post slides to the end of the groove near the protrusion, the second limiting boss and the first limiting boss are aligned and limited, and the pin holes corresponding to the groove and the protrusion are ensured to be coaxial for the insertion of the quick-release pin; when the positioning post slides to the intersection of the groove and the entrance section, the nose adapter frame can be removed. Before the nose adapter frame is inserted into the front edge strip of the fuselage frame, the positioning post is aligned with the entrance section of the positioning groove, which can ensure the misalignment of the first limiting boss and the second limiting boss, and enable the protrusion to enter the groove, preventing the second limiting boss and the first limiting boss from interfering during blind docking, resulting in the nose adapter frame being unable to enter the front edge strip of the fuselage frame.

[0018] The structure of the present invention can realize the rapid disassembly and assembly of the UAV head and fuselage without the use of tools, can be operated by one person, has a simple and reliable structure, is easy to process, and has low cost, and is particularly suitable for the rapid disassembly and assembly of the cylindrical UAV head. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] 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 of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0020] Figure 1 This is a schematic diagram of the overall structure of a tool-free quick disassembly and assembly head connection structure of the present invention; Figure 2 This is a schematic diagram of an installation application scenario of a tool-free quick-disassembly head connection structure of the present invention; Figure 3 This is a structural diagram of the machine head adapter frame in the present invention; Figure 4 This is a schematic diagram of the front edge strip structure of the fuselage frame in the present invention; Figure 5 This is the structural diagram of the UAV's nose cover; Figure 6 This is the front end structure diagram of the UAV's fuselage skin; Figure 7 This is an exploded view of the overall structure of the structure of the present invention used to connect the nose and fuselage of a drone.

[0021] In the figure: 1. Nose adapter frame, 11. First limiting boss, 12. Groove, 13. First pin hole, 14. Positioning column, 2. Front end edge strip of fuselage frame, 21. Second limiting boss, 22. Bump, 23. Second pin hole, 24. Positioning groove, 3. Quick release pin, 4. Nose cover skin, 5. Front end of fuselage skin, 51. Third pin hole, 52. Positioning slot hole. DETAILED DESCRIPTION

[0022] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. 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 making creative efforts are within the scope of protection of the present invention.

[0023] Example 1: The present invention provides an embodiment of a nose connection structure that can be quickly disassembled without tools, which is used to realize quick disassembly and assembly of the nose and fuselage of a drone without tools. It is mainly suitable for drones that are only provided with a nose cover skin at the nose, without a nose bearing frame supporting the connection between the nose and the fuselage, and the nose cover skin is connected to the fuselage frame.

[0024] like Figure 1 As shown, the tool-free quick-disassembly and assembly nose connection structure includes a nose adapter frame 1 and a front end edge strip 2 of the fuselage frame, which are detachably connected and locked by a quick-release pin 3.

[0025] like Figure 2-Figure 7 As shown, the nose adapter frame 1 is annular, and one end thereof is coaxially embedded in the open end of the nose cover skin 4. The outer diameter wall of this end contacts the inner diameter wall at the edge of the open end of the nose cover skin 4. The two are fixed by gluing or screwing, so that the nose adapter frame 1 and the nose cover skin 4 form an integral structure. The other end of the nose adapter frame 1 needs to be detachably docked with the front end edge strip 2 of the fuselage frame. Therefore, a structure design for detachable docking is performed on this end and the front end edge strip 2 of the fuselage frame. The front end edge strip 2 of the fuselage frame is located at the end of the UAV fuselage close to the nose, and belongs to the front end part of the fuselage frame. The fuselage frame is covered with a fuselage skin. For the sake of convenience of description, the fuselage skin located outside the front end edge strip 2 of the fuselage frame is referred to as the front end 5 of the fuselage skin, which is the front end part of the fuselage skin. The front end edge strip 2 of the fuselage frame is embedded in the fuselage skin, providing fuselage structural support and internal load-bearing support, and is used to connect with the nose to support the nose. One end of the head adapter frame 1 that is connected to the front edge strip 2 of the fuselage frame is coaxially embedded in the front edge strip 2 of the fuselage frame to achieve connection.

[0026] Specifically, such as Figure 3 As shown, at the radially outer edge of the nose adapter frame 1, where it is embedded in one end of the front end edge strip 2 of the fuselage frame, six first position-limiting bosses 11 are evenly distributed around the circumference. A radially inwardly concave groove 12 is provided between two adjacent first position-limiting bosses 11, and a first pin hole 13 is radially provided at the center of the bottom of the groove 12. The top of the groove 12 is open toward one end of the front end edge strip 2 of the fuselage frame, and is configured to mate with a corresponding protrusion 22 provided on the front end edge strip 2 of the fuselage frame. A positioning post 14 is provided adjacent to the groove 12. The positioning post 14 is radially fixed to the outer diameter surface of the nose adapter frame 1 and is configured to mate with a corresponding positioning groove 24 provided on the front end edge strip 2 of the fuselage frame.

[0027] like Figure 4 As shown, six second stopper bosses 21 are evenly distributed around the radial inner surface of the front edge of the fuselage frame 2, facing the nose adapter frame 1. These second stopper bosses 21 correspond one-to-one with the first stopper bosses 11. A radially inwardly projecting block 22 (projecting toward the axis) is located between two adjacent second stopper bosses 21. A second pin hole 23 is located in the middle of each block 22, radially extending along the front edge of the fuselage frame 2. A positioning slot 24 is located adjacent to the block 22, corresponding to the positioning post 14. Because the front edge of the fuselage frame 2 is fully embedded in and fixedly connected to the fuselage skin, a third pin hole 51 and a positioning slot 52 are provided at the front end 5 of the fuselage skin. The third pin hole 52 and the second pin hole 23 are coaxial and of the same size. The positioning slot 52 and the positioning slot 24 are identical in structure and coaxial, facilitating the installation of the quick-release pin 3 and the coordinated use of the positioning post 14 and the positioning slot 24.

[0028] When the nose adapter frame 1 and the front end edge strip 2 of the fuselage frame are docked, the positioning column 14 and the positioning groove 24 are relative, so that the first limiting boss 11 and the second limiting boss 21 are misaligned to avoid interference, and at the same time, the protrusion 22 falls into the groove width range of the groove 12, and the nose adapter frame 1 (with the nose cover skin 4) is inserted into the front end edge strip 2 of the fuselage frame, and then the nose cover skin 4 is rotated to make the positioning column 14 slide circumferentially in the positioning groove 24 until it is limited by the positioning groove 24. At this time, the nose adapter frame 1 and the front end edge strip 2 of the fuselage frame are docked in place, the first pin hole 13 and the second pin hole 23 are coaxial, the first limiting boss 11 is located on the inner side of the second limiting boss 21, and the second limiting boss 21 forms an axial limit on the first limiting boss 11, and then the quick-release pin 3 is inserted from the outside to the inside in sequence into the third pin hole 51, the second pin hole 23 and the first pin hole 13 to achieve locking. The quick release pin 3 adopts the navigation mark hb6864-2011 quick release lock pin. The quick release pin 3 is vertically inserted into the pin hole to prevent the nose adapter frame and the front end edge strip of the fuselage frame from rotating relative to each other, and can further limit the axial direction to prevent the nose adapter frame from falling out from the front end edge strip of the fuselage frame.

[0029] In this embodiment, the length, width, and protrusion height of the first limiting boss 11 and the second limiting boss 21 are the same. The length and width of the first limiting boss 11 and the second limiting boss 21 are both 14mm x 7mm, and the protrusion height is both 2mm. When the nose adapter frame 1 and the front end edge strip 2 of the fuselage frame are docked in place, the first limiting boss 11 and the second limiting boss 21 are aligned along the heading, that is, aligned along the axial direction. Alignment is achieved by the positioning groove 24 limiting the sliding limit position of the positioning column 14 when the nose adapter frame 1 rotates relative to the front end edge strip 2 of the fuselage frame. In order to ensure the smooth rotation of the nose adapter frame 1 relative to the front end edge strip 2 of the fuselage frame, a gap of 0.5mm-1mm is left between the first limiting boss 11 and the second limiting boss 21 when the nose adapter frame 1 and the front end edge strip 2 of the fuselage frame are docked in place. The number, size, and arrangement of the first limiting boss 11 and the second limiting boss 21 can be adjusted according to actual conditions.

[0030] The positioning groove 24 cooperates with the positioning column 14 to form an angular positioning at the initial stage of docking between the head adapter frame 1 and the front edge strip 2 of the fuselage frame, avoiding the interference between the second limiting boss 21 and the first limiting boss 11 when docking at any angle. At the same time, it also limits the depth of the head adapter frame 1 embedded in the front edge strip 2 of the fuselage frame. On the other hand, it can also limit the rotation of the head adapter frame 1 relative to the front edge strip 2 of the fuselage frame, so that the first pin hole 13 and the second pin hole 23 are coaxial, and the second limiting boss 21 and the first limiting boss 11 are aligned to form an axial limit. Figure 4 As shown, the positioning groove 24 is a T-shaped hollow structure that radially passes through the front edge strip 2 of the fuselage frame. The positioning groove 24 includes an entrance section and a channel section. The entrance section opens toward the positioning post 14 and is used for positioning and docking with the positioning post 14. The channel section is arranged along the circumferential arc surface of the front edge strip 2 of the fuselage frame. The channel section is used for the positioning post 14 to slide within the channel. The end of the channel section forms a limit for the sliding of the positioning post 14. That is, when the positioning post 14 slides to the end of the channel near the protrusion 22, the second limiting boss 21 and the first limiting boss 11 are aligned and limited, and the first pin hole 13 and the second pin hole 23 are coaxial to facilitate the insertion of the quick-release pin 3. When the positioning post 14 slides to the intersection of the channel section and the entrance section, the head adapter frame 1 can be removed.

[0031] Example 2: This embodiment provides a tool-free quick disassembly and assembly method for the nose and fuselage of a drone, and the drone is equipped with the tool-free quick disassembly and assembly nose connection structure described in Example 1. The nose of the drone is a nose cover skin 4 of a non-load-bearing structure, a fuselage frame is provided inside the fuselage, and the fuselage skin is wrapped and fixed outside the fuselage frame. The nose adapter frame 1 is fixedly installed at the open end of the nose cover skin 4, and the front end edge strip 2 of the fuselage frame is fixedly installed in the fuselage skin. Since the front end edge strip 2 of the body frame is completely embedded in the fuselage skin, a third pin hole 51 and a positioning slot hole 52 are provided at the front end 5 of the fuselage skin. The third pin hole 51 and the second pin hole 23 are coaxial and have the same size, and the positioning slot hole 52 and the positioning slot 24 have the same structure and are coaxial, so as to facilitate the installation of the quick-release pin 3 and the use of the positioning column 14. The specific method includes: During installation, align the positioning column 14 and the entrance section of the positioning groove 24, and push the nose cover skin 4 toward the fuselage. When the positioning column 14 enters the groove section of the positioning groove 24, rotate the nose cover skin 4 to make the positioning column 14 slide to the end of the groove section close to the end of the protrusion 22. At this time, the second pin hole 23 of the protrusion 22 and the first pin hole 13 of the groove 12 are coaxial, and the first limiting boss 11 and the second limiting boss 21 are aligned along the heading. Insert the quick-release pin 3 from the outside to the inside into the third pin hole 51, the second pin hole 23 and the first pin hole 13 in turn to achieve locking, completing the connection and installation of the nose and the fuselage.

[0032] During disassembly, remove the quick-release pin 3, rotate the nose cover skin 4 in the opposite direction, and slide the positioning column 14 to the intersection of the groove section and the entrance section. At this time, the first limiting boss 11 disengages from the axial limit of the second limiting boss 21, and pulls the nose cover skin 4 outward to make the nose adapter frame 1 detach from the front end edge strip 2 of the body frame, completing the disassembly of the nose and the fuselage.

[0033] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A tool-free quick disassembly and assembly head connection structure, characterized in that: include: Nose adapter frame and front edge strip of fuselage frame; The nose adapter frame is annular, one end of which is coaxially embedded in the open end of the nose cover skin and fixedly connected to the edge of the open end of the nose cover skin, and the other end of which is coaxially embedded in the front end edge strip of the fuselage frame and detachably connected to it; Among them, the nose adapter frame is embedded in the radial outer surface of one end of the front end edge strip of the fuselage frame, and a plurality of first limiting bosses are evenly distributed along a circle. A radially inwardly concave groove is provided between two adjacent first limiting bosses, and a first pin hole is provided at the center of the bottom of the groove; a plurality of second limiting bosses are evenly distributed around the radial inner surface of the front end edge strip of the fuselage frame toward one end of the nose adapter frame, and the second limiting bosses correspond to the first limiting bosses one by one. A radially inwardly convex block is provided between two adjacent second limiting bosses, and a second pin hole is provided in the middle of the block along the radial direction; When the head adapter frame and the front end edge strip of the fuselage frame are docked in place, the protrusion is located in the groove, the first pin hole and the second pin hole are coaxial and fixed by quick-release pins, the first limiting boss is located on the inner side of the second limiting boss, and the second limiting boss forms an axial limit on the first limiting boss.

2. The tool-free quick-disassembly head connection structure according to claim 1, characterized in that: The length, width and protrusion height of the first limiting boss and the second limiting boss are the same. When the nose adapter frame and the front end edge strip of the fuselage frame are docked in place, the first limiting boss and the second limiting boss are aligned along the heading.

3. The tool-free quick-disassembly head connection structure according to claim 2, characterized in that: When the nose adapter frame and the front end edge strip of the fuselage frame are butt-jointed, a gap of 0.5 mm to 1 mm exists between the first limiting boss and the second limiting boss.

4. The tool-free quick-disassembly head connection structure according to claim 1, characterized in that: The top of the groove and one end facing the front edge of the fuselage frame are open and are used to dock with the protrusion; the groove width is greater than the width of the protrusion, which is used to ensure that when the first limiting boss is misaligned with the second limiting boss, the protrusion can fall into the groove, and when the first limiting boss and the second limiting boss are aligned along the heading, the second pin hole of the protrusion and the first pin hole of the groove are coaxial.

5. The tool-free quick-disassembly head connection structure according to claim 1, characterized in that: A positioning post is provided next to the groove of the head adapter frame, and the positioning post is fixed on the outer diameter surface of the head adapter frame along the radial direction. A positioning groove is provided next to the protrusion of the front end edge strip of the fuselage frame, and the positions of the positioning groove and the positioning post correspond to each other; when the head adapter frame and the front end edge strip of the fuselage frame are docked, the positioning post is inserted into the positioning groove, and the positioning groove and the positioning post cooperate to limit the angular position of the head adapter frame and the front end edge strip of the fuselage frame when they are docked.

6. The tool-free quick-disassembly head connection structure according to claim 5, characterized in that: The positioning groove is a T-shaped hollow structure, including an entrance section and a groove section. The entrance section faces the positioning column, and the entrance section is used to position and dock with the positioning column. The groove section is arranged along the circumferential arc surface of the front end edge strip of the fuselage frame. The groove section is used for the positioning column to slide in the groove, and the end of the groove section forms a sliding limit for the positioning column.

7. The tool-free quick-disassembly head connection structure according to claim 1, characterized in that: The nose adapter frame is fixed to the edge of the opening end of the nose cover skin by gluing or screwing.

8. A drone, characterized in that: The nose connection structure for quick disassembly and assembly without tools as described in claim 6 is adopted, and the front end edge strip of the body frame is completely embedded in the fuselage skin. A third pin hole and a positioning slot are provided at the front end of the fuselage skin. The third pin hole and the second pin hole are coaxial and have the same size, and the positioning slot and the positioning slot of the front end edge strip of the fuselage frame have the same structure and are coaxial.

9. A tool-free rapid disassembly and assembly method for the nose and fuselage of a UAV according to claim 8, characterized in that: The nose adapter frame is installed at the open end of the nose cover skin, and the front edge strip of the body frame is installed in the fuselage skin. The method includes: During installation, align the positioning post with the entrance section of the positioning slot and push the nose cover toward the fuselage. When the positioning post enters the groove section of the positioning slot, rotate the nose cover so that the positioning post slides to the end of the groove section close to the protruding end. At this time, insert the quick-release pin from the outside to the inside in sequence into the third pin hole, the second pin hole, and the first pin hole to lock the connection between the nose and the fuselage. During disassembly, remove the quick-release pin, rotate the nose cover skin in the opposite direction, and slide the positioning column to the intersection of the groove section and the entrance section. At this time, pull the nose cover skin outward to make the nose adapter frame detach from the front edge strip of the body frame, completing the separation and disassembly of the nose and fuselage.

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