A method for quick installation, locking and dismounting of a tail boom of an unmanned helicopter

Abstract

The present application relates to a kind of unmanned helicopter tail beam quick installation locking and dismounting method, belong to unmanned aerial vehicle technical field, solve the technical problem that unmanned helicopter tail beam cannot reliably and main body of fuselage quick installation locking and dismounting, inconvenient storage and transportation.The quick installation locking method steps of the present application include: preparing tail beam assembly in tail beam component, preparing tail beam quick release body, tail beam quick release body is installed to tail beam assembly, preparing fuselage butt joint spacer, fuselage butt joint spacer is connected at the inner edge of the tail end of main body of fuselage, tail beam component is quickly connected to fuselage butt joint spacer by quick release tool component, realize the quick connection of unmanned helicopter tail beam and main body of fuselage.The present application can realize quick installation locking and dismounting tail beam from main body of fuselage, save manpower and time, guarantee convenient maintenance and quick response, so that installation performance can guarantee product consistency.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a method for the rapid installation, locking, and disassembly of the tail boom of an unmanned helicopter. Background Technology

[0002] The tail boom of a single-rotor unmanned helicopter with a tail rotor is mainly used to transmit the anti-torque generated by the tail rotor and to provide a support structure for the horizontal and vertical tails, transmitting the aerodynamic loads of the horizontal and vertical tails; at the same time, a transmission device needs to be installed inside the tail boom to transmit power to the tail rotor, so the tail boom needs a certain amount of internal space.

[0003] The tail boom of a coaxial twin-rotor unmanned helicopter is mainly used to provide a support structure for the horizontal and vertical tails, transmit the inertial and aerodynamic loads of the horizontal and vertical tails, and at the same time provide installation space for other equipment on the aircraft.

[0004] It is evident that the tail boom, as an important module of unmanned helicopters, needs not only sufficient internal space but also sufficient strength and rigidity.

[0005] Currently, most unmanned helicopters on the market adopt a truss-type tail boom structure, generally welded from stainless steel or titanium alloy rods, and covered with a flow-rectifying and drag-reducing skin. This structure has low cost and is easy to withstand concentrated loads. However, such tail booms have poor bending and torsional resistance, requiring diagonal support rods to improve rigidity, followed by the addition of skin and fasteners. This makes the unmanned helicopter structure complex, the skin prone to damage, the structural weight efficiency low, and product inconsistency poor. Furthermore, in order to reduce weight and create more internal space, thin-walled rods are usually selected, resulting in insufficient tail boom rigidity, limited effective internal space, and unfavorable conditions for the layout and installation of transmission devices or other onboard equipment.

[0006] In addition, the tail boom of conventional unmanned helicopters is usually large, and in order to save storage and transportation space for unmanned helicopters, the tail boom needs to be disassembled.

[0007] Currently, the tail boom of unmanned helicopters is typically connected to the fuselage using conventional fasteners such as bolts. To ensure installation reliability, multiple sets of bolts are required for tightening, resulting in lengthy installation and disassembly times. This is inconvenient for helicopter maintenance and emergency response. Therefore, there is an urgent need for a safe, reliable, and convenient tail boom disassembly and installation solution. Summary of the Invention

[0008] Based on the above analysis, the present invention aims to provide a method for the rapid installation, locking, and disassembly of the tail boom of an unmanned helicopter, in order to solve the technical problems of time-consuming and labor-intensive installation and disassembly of the fuselage, and the inability to guarantee product consistency in installation performance.

[0009] This invention is achieved through the following technical solution:

[0010] A method for quickly installing and locking the tail boom of an unmanned helicopter, characterized by comprising the following steps:

[0011] S1. Prepare the tail beam assembly in the tail beam components;

[0012] S2. Prepare the quick-release body of the tail beam quick-release assembly in the tail beam component;

[0013] S3. Install the quick-release tail beam onto the tail beam assembly;

[0014] S4. Prepare the fuselage docking frame;

[0015] S5. Connect the fuselage docking frame to the inner edge of the rear end of the main fuselage body;

[0016] S6. Using the quick-release tool, the tail beam component is quickly connected to the fuselage docking frame, achieving a rapid connection with the main body of the fuselage.

[0017] Furthermore, S1 includes connecting the first movable hinge, the left reinforcing body, and the right reinforcing body to the tail beam skin.

[0018] Furthermore, in S2, the tail beam quick-release body has an annular groove structure. The outer periphery of the annular groove structure of the tail beam quick-release body is integrally shaped into the inner side of the tail beam skin head, with a gap set at the inner side of the tail beam skin head. Furthermore, S2 includes installing a tail beam connector on the platform on the outer periphery of the annular groove structure of the tail beam quick-release body, and connecting a left and right pin lock body to the outer surface of the bottom of the annular groove of the tail beam quick-release body.

[0019] Furthermore, S3 includes installing the tail beam quick-release body onto the tail beam assembly via a first set of fasteners and a second set of fasteners.

[0020] Furthermore, the docking frame in S4 includes a docking frame body and a docking frame connecting assembly; the docking frame body is an annular groove structure, and the outer peripheral side of the docking frame body is shaped into the inner side of the tail end of the main body; the docking frame connecting assembly includes a second movable hinge, a left locking latch, a right locking latch, and a protective body; S3 includes connecting the second movable hinge, the left locking latch, the right locking latch, and the protective body to the docking frame body.

[0021] Furthermore, S5 includes an outer groove of the docking frame aligned with the rear end of the fuselage body and connected to the rear end of the fuselage body.

[0022] Furthermore, the tool component in S6 includes a movable hinge tool and two symmetrically mounted left and right latches; S6 includes connecting the two latches to the left latch and the right latch respectively, and mounting the movable hinge tool at the hinge joint of the first movable hinge and the second movable hinge.

[0023] Furthermore, S6 includes actuating the movable hinge tool to form the upper quick-release connecting hinge lock, and actuating the two bolt locks to form the left and right lock body locking structures.

[0024] Furthermore, a method for quickly disassembling the tail boom of an unmanned helicopter, used to quickly disassemble the tail boom of the unmanned helicopter installed at the rear end of the fuselage, includes the following steps:

[0025] T1. Use the tool to connect the movable hinge to separate the upper quick-release hinge:

[0026] T2. Move the bolt lock to separate the left and right lock body locking structures;

[0027] T3, separate the main fuselage and tail boom components.

[0028] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0029] 1. The method of the present invention can ensure good assembly processability and good product consistency between the tail boom and the fuselage body of the unmanned helicopter.

[0030] 2. The method of the present invention uses a hinge and locking mechanism for the installation, locking and disassembly of the tail boom and fuselage of the unmanned helicopter, which can realize the function of quick disassembly and installation of the tail boom of the unmanned helicopter, saving manpower and time costs.

[0031] 3. The method of the present invention makes it possible to quickly disassemble and install the tail beam, which facilitates the inspection and maintenance of the whole machine in case of emergencies and can also make a rapid response to emergency use.

[0032] 4. The method of the present invention can realize the rapid disassembly of the tail boom of the unmanned helicopter from the main structure of the unmanned helicopter, which facilitates the separate storage and transportation of the unmanned helicopter and saves storage and transportation costs.

[0033] Other features and advantages of the invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained from what is particularly pointed out in the description and the drawings. Attached Figure Description

[0034] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0035] Figure 1 This is a flowchart illustrating the steps of a method for quickly locking the tail boom of an unmanned helicopter according to Embodiment 1 of the present invention.

[0036] Figure 2 This is a schematic diagram showing the connection between the tail boom and the main fuselage skin of the quick-release unmanned helicopter of the present invention.

[0037] Figure 3 This is a schematic diagram of the tail beam component structure of the present invention;

[0038] Figure 4 This is a schematic diagram of the tail beam assembly structure of the present invention;

[0039] Figure 5 This is a schematic diagram of the tail beam skin of the present invention connected to the first movable hinge structure via a movable hinge tool;

[0040] Figure 6 This is a schematic diagram of the first movable hinge body structure of the present invention;

[0041] Figure 7 This is a schematic diagram of the tail beam assembly structure of the present invention. Figure 1 ;

[0042] Figure 8 This is a schematic diagram of the tail beam assembly structure of the present invention. Figure 2 ;

[0043] Figure 9 This is a schematic diagram of the movable hinge tool structure of the present invention;

[0044] Figure 10 This is a schematic diagram of the movable hinge tool structure of the present invention;

[0045] Figure 11 This is a schematic diagram of the left bolt lock body structure of the present invention;

[0046] Figure 12 This is a schematic diagram of the installation of the left bolt lock body and the left bolt lock according to the present invention;

[0047] Figure 13 This is a schematic diagram of the installation of the left bolt lock of the present invention;

[0048] Figure 14 This is a schematic diagram of the fuselage docking frame structure of the present invention. Figure 1 ;

[0049] Figure 15 for Figure 14 Schematic diagram of the AA section rotation;

[0050] Figure 16 This is a schematic diagram of the fuselage docking frame structure of the present invention. Figure 2 ;

[0051] Figure 17 This is a schematic diagram of the second movable hinge structure of the present invention;

[0052] Figure 18 This is a schematic diagram of the left locking body structure of the present invention.

[0053] Figure 19This is a flowchart illustrating the steps of a method for quickly disassembling the tail boom of an unmanned helicopter according to Embodiment 3 of the present invention.

[0054] Figure label:

[0055] 1. Tail beam assembly; 11. Tail beam assembly; 111. Tail beam skin; 1111. Lock handle groove; 112. First movable hinge; 1121. First movable hinge body; 11211. First movable hinge hole; 11212. First movable hinge adjustment groove; 11213. First movable hinge mounting hole; 1122. First movable hinge adjusting pad; 113. Left reinforcing body; 114. Right reinforcing body; 12. Tail beam quick-release assembly; 121. Tail beam quick-release body; 122. Tail beam connecting body; 123. Left pin lock body; 1231. Pin lock body base plate; 1232. Pin lock hole; 1233. Limit pin shaft positioning hole; 1234. Movable hinge handle shaft; 1235. Nut guide bushing; 124. Right pin lock body; 2. Body docking frame; 21. Docking frame; 22. Second movable hinge Chain assembly; 221. Second movable hinge body; 2211. Second movable hinge hole; 2212. Second movable hinge mounting hole; 222. Second movable hinge adjusting pad; 23. Left latch; 231. Left latch body; 2311. Left latch hole; 232. Left latch adjusting pad; 24. Right latch; 25. Protective body; 251. Rubber pad; 252. Rubber gasket; 3. Quick-release tool components; 3 1. Movable hinge tool; 311. Movable hinge handle; 312. Movable hinge spring; 32. Pin lock; 321. Pin lock handle; 3211. Handle pivot hole; 322. Pin lock pin; 3221. Pin lock pin limit groove; 3222. Pin lock pin retaining shaft; 323. Pin return compression spring; 324. Pin lock hinge shaft; 325. Limiting pin shaft; 100. Main body skin. Detailed Implementation

[0056] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0057] In this specific embodiment, the front is the direction of the nose of the unmanned helicopter, and the top of the fuselage when it is parked on the ground is the top. The left and right directions are set to be consistent with the left and right directions of a human body when standing in front of the nose and looking at the unmanned helicopter.

[0058] The following is combined Figures 1-19 The technical solution of the present invention will be described in more detail below:

[0059] The method for quick installation, locking, and removal of the tail boom of an unmanned helicopter of the present invention involves quickly installing, locking, or removing a quick-release tail boom of an unmanned helicopter from the fuselage body 100.

[0060] First, combined Figures 2-18 The structure of a detachable tail boom for an unmanned helicopter is described in detail.

[0061] Example 1

[0062] A detachable tail boom for unmanned helicopters.

[0063] like Figure 2 , Figure 3 As shown, the present invention relates to a quick-detachable tail boom for unmanned helicopters, which is used for quick installation or quick disassembly from the fuselage body 100 of the unmanned helicopter.

[0064] like Figure 2 As shown, the head of the quick-detachable tail boom of the unmanned helicopter is detachably connected to the fuselage body 100, and the tail of the quick-detachable tail boom is connected to the horizontal stabilizer 200. The two ends of the horizontal stabilizer 200 are respectively connected to the left vertical stabilizer 300 and the right vertical stabilizer 400. The quick-detachable tail boom, together with the horizontal stabilizer 200, the left vertical stabilizer 300, and the right vertical stabilizer 400, constitutes the tail of the unmanned helicopter. The quick-detachable tail boom allows for rapid assembly and disassembly of the fuselage body 100 and the tail of the unmanned helicopter, facilitating separate storage and transportation, rapid maintenance, and a rapid response to emergency use.

[0065] The quick-release tail boom of the unmanned helicopter includes a tail boom component 1, a fuselage docking frame component 2, and a quick-release tool component 3. The tail boom component 1 and the fuselage docking frame component 2 have corresponding connecting structures, allowing for quick installation or disassembly using the quick-release tool component 3. The fuselage docking frame component 2 is fixedly connected to the tail edge of the fuselage body 100.

[0066] like Figure 3 As shown, the tail beam component 1 includes a tail beam assembly 11 and a tail beam quick-release assembly 12.

[0067] like Figure 4 As shown, the tail beam assembly 11 includes a tail beam skin 111, a first movable hinge 112, a left reinforcing body 113, and a right reinforcing body 114.

[0068] like Figure 7 As shown, the tail beam quick-release assembly 12 includes a tail beam quick-release body 121 and a tail beam connecting unit, with the tail beam connecting unit connected to the tail beam quick-release body 121.

[0069] Specifically, the tail beam connection unit includes a tail beam connector 122, a left pin lock body 123, and a right pin lock body 124.

[0070] like Figure 14As shown, the fuselage docking bulkhead component 2 includes a docking frame 21 and a docking frame connecting assembly. The docking frame connecting assembly is connected to the docking frame 21 and includes a second movable hinge 22, a left locking latch 23, a right locking latch 24, and a protective body 25.

[0071] like Figure 3 As shown, the quick-release tool component 3 includes a movable hinge tool 31 and two symmetrically mounted bolt locks 32 on the left and right.

[0072] Specifically:

[0073] like Figure 4 As shown, the tail boom skin 111 of the tail boom assembly 11 is a sleeve structure with an internal liner. The tail boom skin 111 adopts a carbon fiber composite honeycomb sandwich structure with high specific strength and specific stiffness, which minimizes the weight of the unmanned helicopter while ensuring strength and stiffness. The tail boom skin 111 adopts integral molding technology, which has good assembly processability and good product consistency.

[0074] Symmetrical lock handle grooves 1111 are provided along the lower edge of the tail beam skin 111, allowing the bolt handles 321 of the two identical bolt locks 32 on the left and right to pass through the tail beam skin 111 for easy operation by the installer. A partial platform with skin mounting holes is provided along the upper edge of the tail beam skin 111 for connecting the first movable hinge 112 via fasteners.

[0075] like Figure 5 As shown, the first movable hinge 112 is connected to the upper outer side of the tail boom skin 111 and is centrally located. The first movable hinge 112 includes a first movable hinge body 1121 and a first movable hinge adjusting pad 1122. The shape of the first movable hinge adjusting pad 1122 is consistent with the bottom plane of the first movable hinge body 1121. In the installed state, the first movable hinge adjusting pad 1122 is located between the outer side of the head of the tail boom skin 111 and the bottom plane of the first movable hinge body 1121, and is used to adjust the assembly clearance of the quick-release unmanned helicopter tail boom.

[0076] Specifically, the first movable hinge body 1121 includes an integrally formed flat plate and a first movable hinge shaft with a first movable hinge hole 11211 provided on one side of the flat plate.

[0077] The axis of the first movable hinge hole 11211 is above the plate and parallel to the plate. The radius of the first movable hinge hole 11211 is equal to the vertical distance from the axis of the cylinder to the upper surface of the plate.

[0078] The first movable hinge body 1121 has multiple first movable hinge mounting holes 11213 on its flat surface. The positions of the first movable hinge mounting holes 11213 match the skin mounting holes. They are used to connect the first movable hinge body 1121 to the tail beam skin 111 through the first set of fasteners, and at the same time, they are connected to the tail beam quick-release assembly 12 through the tail beam connector 122.

[0079] like Figure 6 As shown, two first movable hinge adjustment grooves 11212 are symmetrically and evenly distributed on the cylinder of the first movable hinge body 1121. The first movable hinge adjustment groove 11212 includes an axial groove at the top of the cylinder of the first movable hinge body 1121, and a circumferential groove with a 90° arc at both ends of the axial groove. The first movable hinge adjustment groove 11212 communicates with the first movable hinge hole 11211, and the two ends of the circumferential groove open towards the flat plate of the first movable hinge body 1121 and open onto the flat plate of the first movable hinge body 1121; the first movable hinge adjustment groove 11212 thus forms a double ear groove within a 90° range, forming two limiting positions of the movable hinge tool 31 at this time. When the movable hinge tool 31 is located in the relatively outer ear groove, it corresponds to the installation position of the tail boom and fuselage of the unmanned helicopter. When the movable hinge tool 31 is located in the relatively inner groove, it corresponds to the detachable position of the tail boom and fuselage of the unmanned helicopter. Here, the movable hinge tool 31 and the first movable hinge body 1121 form part of the upper quick-release connecting hinge locking structure.

[0080] Preferably, the radial groove and axial groove of the first movable hinge adjustment groove 11212 are of equal width and smaller than the diameter of the first movable hinge hole 11211. More preferably, the width of the radial groove and axial groove of the first movable hinge adjustment groove 11212 is the radius value of the first movable hinge hole 11211.

[0081] like Figure 4 and Figure 8 As shown, the left reinforcing body 113 and the right reinforcing body 114 are mirror-symmetrical components, both having an open slot structure with a bottom end face at one end. The bottom end face is located on one side of the fuselage body 100 and is positioned behind the local platform set on the tail boom skin 111. The open slots of the left reinforcing body 113 and the right reinforcing body 114 are symmetrically arranged opposite each other at the central axis of the inner side of the head of the tail boom skin 111 and extend into the tail boom skin 111.

[0082] Taking the left-hand reinforced body 113 as an example:

[0083] In the installed state, the outer surface of the left reinforcing body 113 is stepped, with the smaller part close to the bottom end face to be locked in the slot of 121; the larger part has the same shape as the inner side of the tail beam skin 111 and is connected to the tail beam skin 111 through this surface.

[0084] Preferably, in this embodiment, the left reinforcing body 113 is riveted to the tail beam skin 111 at a portion that has the same shape as the inner side of the tail beam skin 111.

[0085] The front end face of the left reinforcing body 113 is flat, and the front end face of the left reinforcing body 113 is provided with multiple evenly distributed reinforcing body mounting holes, which are connected to the tail beam quick-release assembly 12 through the second set of fasteners.

[0086] The structure and connection relationship of the right reinforcing body 114 are mirror images of the left reinforcing body 113.

[0087] The left reinforcing body 113 and the right reinforcing body 114, which have a bottom end opening groove structure, serve as support and connecting bodies and are set inside the tail beam skin 111 of the shell, which can enhance the structural strength and connection strength of the tail beam skin 111 at this location.

[0088] like Figure 7 and Figure 8 As shown, the quick-release body 121 of the tail beam has a ring groove structure.

[0089] The annular groove structure of the tail beam quick-release body 121 is integrally shaped on the inner side of the tail beam skin 111 after the edge of the partial platform, and is spaced apart on the inner side of the tail beam skin 111 after the edge of the partial platform. The groove is inserted into the sleeve of the tail beam skin 111 from the front end in a rearward direction. The left reinforcing body 113 and the right reinforcing body 114 are inserted into the annular groove of the tail beam quick-release body 121, so that the bottom of the annular groove of the tail beam quick-release body 121 abuts against the horizontal bottom end face of the left reinforcing body 113 and the right reinforcing body 114. The tail beam quick-release body 121 is provided with a tail beam quick-release body connection hole that matches the reinforcing body mounting hole. The tail beam quick-release body 121 is connected to the left reinforcing body 113 and the right reinforcing body 114 through a second set of fasteners, thereby connecting the tail beam quick-release body 121 and the tail beam skin 111 into a whole. The tail boom skin 111 can be connected to the fuselage body 100 via the tail boom quick-release body 121.

[0090] like Figure 7 As shown, the tail beam connector 122 is a curved plate structure with two reinforcing ribs, and the bending angle is 90°. One of the two adjacent right-angled surfaces is connected to the outer bottom surface of the annular groove of the tail beam quick-release body 121, so that after the tail beam connector 122 is connected to the left reinforcing body 113 and the right reinforcing body 114, the other plane of the two adjacent vertical surfaces is located at the inner surface of the local platform of the tail beam skin 111, and is provided with multiple mounting holes that match the first movable hinge mounting holes 11213.

[0091] The tail beam connector 122 with a reinforced rib plate structure has structural strength and is located inside the local platform of the tail beam skin 111 in the installed state, for mounting the first movable hinge body 1121.

[0092] Preferably, in this embodiment, one plane of the tail beam connector 122 is riveted to the outer bottom surface of the annular groove of the tail beam quick-release body 121, one plane of the tail beam connector 122 contacts the inner surface of the partial platform of the tail beam skin 111, and is provided with a tail beam connector mounting hole that matches the skin mounting hole. The first set of fasteners simultaneously connects the tail beam connector 122, the tail beam skin 111 and the first movable hinge body 1121.

[0093] like Figure 7 As shown, at the positions corresponding to the left reinforcing body 113 and the right reinforcing body 114, on the outer bottom surface of the annular groove of the tail beam quick-release body 121, there are symmetrically arranged left pin lock body 123 and right pin lock body 124 with structural mirror symmetry.

[0094] Taking the left bolt lock body 123 as an example:

[0095] like Figure 11 As shown, the left bolt lock body 123 is an integrally molded part, including a bolt lock body base plate 1231. The bolt lock body base plate 1231 is provided with a bolt lock body base plate mounting hole. The bolt lock body base plate, the tail beam quick release body 121 and the left reinforcing body 113 / or the right reinforcing body 114 are connected by a second set of fasteners.

[0096] The tail beam quick-release body 121 is connected to the tail beam skin 111 as a whole.

[0097] A latch lock body axle is provided on the latch lock body base plate 1231. A latch lock hole 1232 is provided on the latch lock body axle. A limit pin positioning hole 1233 is provided radially along the latch lock hole 1232 and perpendicular to the side of the latch lock body axle. The limit pin positioning hole 1233 is specifically located near the second end of the limit pin positioning hole 1233. A movable hinge handle shaft 1234 is also provided on the latch lock body base plate 1231. The movable hinge handle shaft 1234 is separately provided from the latch lock body axle. The movable hinge handle shaft 1234 is a stepped shaft. The small shaft of the stepped shaft is provided with a handle shaft pin hole.

[0098] Preferably, to reduce weight, the pin lock body axle in this embodiment is configured as a hollow structure, that is, the pin lock body axle has a groove inside, the groove wall thickness is the same as the pin lock body base plate 1231, and the pin lock hole 1232 is essentially two corresponding pin lock shaft holes on opposite wall surfaces.

[0099] Preferably, a stepped shaft hole is made at the right side of the left pin lock body 123 pin lock hole 1232 end, and the outer larger shaft hole wall is set as a threaded hole for screwing the nut guide bushing 1235; the inner surface of the nut guide bushing 1235 is hardened, which can well realize the positioning and guiding function.

[0100] It should be noted that a partial platform matching the head of the tail boom skin 111 is provided on the upper part of the tail end of the fuselage body 100, which is used to smoothly connect the tail boom skin 111 and connect the quick-release structural components.

[0101] like Figure 14 , Figure 15 and Figure 16 As shown, the outer periphery of the docking frame 21 is fixed to the inner edge of the tail end of the main body 100, and the docking frame connecting component 22 is connected to the docking frame 21.

[0102] Specifically, the docking frame 21 is an annular groove structure. The outer periphery of the docking frame 21 is shaped and set on the inner side of the tail end of the fuselage body 100. The upper part of the annular groove structure is provided with a docking frame platform corresponding to the position of the local platform above the head of the tail beam skin 111.

[0103] The docking frame 21 is inserted into the sleeve of the main body 100 from the rear end of the main body 100 with the groove facing forward, and is connected to the rear end of the main body 100. The outer plane of the bottom of the annular groove of the docking frame 21 is flush with the rear end of the main body 100.

[0104] Preferably, in this embodiment, the connection method between the docking frame 21 and the main body 100 is riveting.

[0105] like Figure 14 As shown, a second movable hinge assembly 22 is provided on the docking frame platform of the docking frame 21. The second movable hinge assembly 22 includes a second movable hinge body 221 and a second movable hinge adjusting pad 222. The shape of the second movable hinge adjusting pad 222 is consistent with the bottom plane of the second movable hinge body 221; in the installed state, the second movable hinge adjusting pad 222 is located between the lower surface of the second movable hinge body 221 and the upper surface of the docking frame 21, and is used to adjust the assembly clearance of the quick-release unmanned helicopter tail boom.

[0106] The second movable hinge body 221 has a structure that matches and connects with the first movable hinge body 1121.

[0107] like Figure 17 As shown, the second movable hinge body 221 has multiple second movable hinge mounting holes 2212 on its flat plate; matching the second movable hinge mounting holes 2212, the docking frame platform of the docking frame body 21 also has multiple docking frame mounting holes, and the second movable hinge body 221 is connected to the docking frame body 21 through a third set of fasteners.

[0108] like Figure 17As shown, the second movable hinge body 221 includes an integrally formed flat plate and two opposing second movable hinge shafts with second movable hinge holes 2211 on both ends of one side of the flat plate; the distance between the two second movable hinge shafts is equal to the first movable hinge shaft on the first movable hinge body 1121, and the second movable hinge holes 2211 have the same diameter as the first movable hinge holes 11211.

[0109] Combination Figure 2 and Figure 5 As shown, the two outer end faces of the first movable hinge shaft mate with the inner end faces of the two second movable hinge shafts to form the rotating shaft hole for the upper quick-release connecting hinge of the tail beam assembly 11 and the fuselage docking frame 2. The movable hinge tool 31 connects the first movable hinge body 1121 and the second movable hinge body 221 to form the upper quick-release connecting hinge.

[0110] like Figure 9 As shown, the movable hinge tool 31 includes a movable hinge handle 311 and a movable hinge spring 312. The movable hinge spring 312 is a compression spring, and the outer diameter of the movable hinge spring 312 is the same as the diameter of the second movable hinge hole 2211 and the first movable hinge hole 11211.

[0111] In the installed state, the movable hinge spring 312 is extended, and the movable hinge insertion posts of the two movable hinge handles 311 are located in the rotating shaft holes of the upper quick-release connecting hinge, with their ends locked in the second movable hinge hole 2211. The movable hinge handle posts of the two movable hinge handles 311 are located in the ear grooves on the outer side of the first movable hinge adjustment groove 11212, and are parallel to the plate of the first movable hinge body 1121.

[0112] When quick release is required, the movable hinge handle posts of the two movable hinge handles 311 rotate upwards by 90°, entering the axial groove of the first movable hinge adjustment groove 11212, and shifting relative to each other, compressing the movable hinge spring 312 until they reach the ear groove on the inner side of the first movable hinge adjustment groove 11212. Then, they rotate back 90°, and the movable hinge handle posts of the two movable hinge handles 311 are set parallel to the flat plate of the first movable hinge body 1121 at the inner ear groove. At this time, the movable hinge insertion posts of the two movable hinge handles 311 retract from the second movable hinge hole 2211, and the first movable hinge body 1121 and the second movable hinge body 221 are disconnected at the upper quick-release connecting hinge.

[0113] Preferably, the movable hinge spring 312 is clearance-fitted with the second movable hinge hole 2211 and the first movable hinge hole 11211.

[0114] Specifically, the movable hinge handle 311 is composed of two columns with perpendicular axes, namely the movable hinge insertion column and the movable hinge handle column. It can be integrally formed, or the movable hinge handle column can be fastened to the movable hinge insertion column; preferably, the movable hinge handle column is screwed to the movable hinge insertion column.

[0115] Preferably, the movable hinge insertion post and the first movable hinge hole 11211 are clearance-fitted; the diameter of the movable hinge handle post is not greater than the radial groove width of the first movable hinge adjustment groove 11212. More preferably, the radial groove width of the first movable hinge adjustment groove 11212 is equal to the diameter of the movable hinge handle post and smaller than the diameter of the first movable hinge hole 11211.

[0116] The movable hinge tool 31 cooperates with the upper quick-release connecting hinge to form a movable hinge locking structure.

[0117] like Figure 14 As shown, on the outer plane of the bottom of the annular groove of the docking frame 21, in the installed state, a left latch 23 and a right latch 24 are connected corresponding to the positions of the latch holes 1232. The structure and connection relationship of the left latch 23 and the right latch 24 are mirror symmetrical.

[0118] Taking the left card lock 23 as an example:

[0119] The left locking mechanism 23 includes a left locking body 231 and a left locking adjustment pad 232.

[0120] like Figure 18 As shown, the left locking body 231 is an integrally formed T-shaped structure plate, including the left locking bottom plate on the bottom of the T and the left locking rib plate of the middle vertical plate of the T.

[0121] Specifically, the left locking base plate has multiple evenly distributed locking base plate connection holes, and correspondingly, the bottom of the annular groove of the docking frame 21 has docking frame locking connection holes. The left locking body 231 is connected to the outer plane of the bottom of the annular groove of the docking frame 21 by a fourth fastener.

[0122] The left locking adjustment pad 232 is set between the left locking body 231 and the outer plane of the bottom of the annular groove of the docking frame 21. Its shape is the same as that of the left locking base plate and it is used to adjust the installation gap.

[0123] Specifically, the left locking rib plate is provided with a left locking hole 2311. In the installed state, the left locking rib plate is attached to the left pin lock body 123, specifically attached to the outer side of the pin lock body axis provided on the pin lock body base plate 1231. The left locking hole 2311 and the pin lock hole 1232 are coaxial and have the same diameter.

[0124] like Figure 7As shown, the bolt lock 32 is installed on the left bolt lock body 123. The bolt lock 32 is inserted into or removed from the left locking hole 2311 on the left locking body 231 through the bolt lock pin 322 from the bolt lock hole 1232 on the left side, connecting or separating the tail beam component 1 and the fuselage docking frame component 2.

[0125] like Figure 10 As shown, the bolt lock 32 is a rocker arm structure assembly, including a bolt lock handle 321, a bolt lock pin 322, a bolt return compression spring 323, a bolt lock hinge shaft 324, and a limit pin shaft 325. The bolt return compression spring 323 is disposed within the bolt lock hole 1232.

[0126] Combination Figure 10 , Figure 12 and Figure 13 As shown, specifically, the latch lock handle 321 has a bent handle structure, with the long end being the operating handle and the short end being the connecting handle.

[0127] At the bend of the latch lock handle 321, there is a handle pivot hole 3211; the latch lock handle 321 is sleeved on the small shaft of the movable hinge handle pivot 1234 through the handle pivot hole 3211, and the large shaft end of the movable hinge handle pivot 1234 and the pin are inserted into the handle pivot pin hole to limit the movement of the latch lock handle 321.

[0128] A hinge shaft hole is provided on the connecting handle of the latch lock handle 321, which is used to movably hinge the first end of the latch lock pin 322 through the latch lock hinge shaft 324; the second end of the latch lock pin 322 passes through the nut guide sleeve 1235 with clearance fit and through the latch lock hole 1232.

[0129] Specifically, a coaxial bearing, specifically a pin locking pin retainer 3222, is provided near the second end of the pin locking pin 3222. The outer diameter of the pin locking pin retainer 3222 matches the inner diameter of the pin locking hole 1232, preferably with a clearance fit. A pin return compression spring 323 is installed between the pin locking pin retainer 3222 and the nut guide sleeve 1235 for limiting and positioning.

[0130] An axial, through-hole locking groove 3221 is provided near the second end of the latch 322, specifically located at the axial position where the positioning hole 1233 of the locking pin is located in the installed state. The width of the locking groove 3221 is not less than the diameter of the locking pin 325. The locking pin 325 passes through the positioning hole 1233 and the locking groove 3221 of the latch body shaft from one end of the latch body shaft, and exits from the other end of the latch body shaft, and is fixed, forming the left lock body locking structure at the left latch body 123.

[0131] Preferably, the width of the locking pin limiting groove 3221 is equal to the stroke of the locking pin 322. The stroke of the locking pin 322 is the axial displacement of the locking pin 322 within the locking pin hole 1232 caused by the rotation of the locking pin handle 321 around the handle pivot 3211 within the lock handle groove 1111.

[0132] In the installed state, under the action of the pin return compression spring 323, the pin locking pin 322 is limited to the position of the limiting pin shaft 325 at the first end of the pin locking pin limiting groove 3221. At this time, the pin locking pin 322 extends the longest distance, and the pin locking pin 322 extends out of the pin locking hole 1232 and penetrates into the left locking hole 2311 of the left locking body 231. The left locking body 231 and the left pin locking body 123 are stably connected here. That is, the connection between the tail beam component 1 and the fuselage docking frame 2 is realized at the left pin locking body 123.

[0133] When it is necessary to disassemble the connection at the left latch lock body 123, simply rotate the latch lock handle 321 clockwise. The latch lock pin 322 moves to the right, and the latch lock pin retaining shaft 3222 compresses the latch return compression spring 323 towards the nut guide sleeve 1235. This causes the latch lock pin 322 to move to the right until the limiting pin shaft 325 is located at the second end of the latch lock pin limiting groove 3221 near the left end. This allows the latch lock pin 322 to completely exit the left latch lock hole 2311 of the left latch lock body 231 and enter the latch lock hole 1232. At this time, the left latch lock body 231 and the left latch lock body 123 are unlocked, realizing the disassembly of the tail beam component 1 and the fuselage docking frame 2. Left latch lock 23

[0134] The structure and connection of the right latch 24 are mirror-symmetrical to the left latch 23. The right-side bolt lock 32 quickly engages or disengages from the right latch 24 via the right bolt lock body 124, forming a right-side locking structure. This allows for the installation and disassembly of the tail beam component 1 and the fuselage docking frame 2 at the right latch 24. The installation and operation of the right latch 24 are the same as those of the left latch 23, except that the bolt lock handle 321 needs to be rotated counterclockwise.

[0135] Preferably, all adjusting shims are multi-layered single-piece structures, which facilitates precise height adjustment and convenient and quick installation.

[0136] like Figure 14 and Figure 15 As shown, a protective body 25 is provided at the middle position of the upper and lower parts of the outer plane of the bottom of the annular groove of the docking frame 21. The protective body 25 includes a rubber pad 251 and a rubber pad 252; the rubber pad 252 is disposed between the bottom surface of the rubber pad 251 and the outer plane of the bottom of the annular groove of the docking frame 21, and has the same shape as the bottom surface of the rubber pad 251.

[0137] Preferably, the rubber pad 251 is composed of multiple layers of rubber pads, which facilitates height adjustment and position adjustment of the rubber pad 251, and reasonably avoids collision damage to the unmanned helicopter during the installation process. In the installed state, the height of the protective body 25 is greater than the distance between the outer plane of the bottom of the annular groove of the docking frame 21 and the outer plane of the bottom of the annular groove of the tail beam quick-release body 121.

[0138] Preferably, the rubber pad 251 is a frustoconical rubber block with a pivot hole for easy passage and fixation of fasteners. Correspondingly, rubber pad mounting holes are provided between the outer plane of the bottom of the annular groove of the docking frame 21. The protective body 25 is connected to the docking frame 21 by fasteners. In the installed state, the top surface of the rubber pad 251 abuts against the outer plane of the bottom of the annular groove of the tail boom quick-release body 121, which serves to reduce friction between the tail boom component 1 and the fuselage docking frame 2, and also has a vibration absorption function, which can further improve the flight quality of the unmanned helicopter.

[0139] Example 2

[0140] Figure 1 A method for quickly locking the tail boom of the unmanned helicopter of Embodiment 1 is shown.

[0141] The steps are as follows:

[0142] S1. Prepare the tail beam assembly 11 in the tail beam component 1;

[0143] S11. Rivet the left reinforcing body 113 and the right reinforcing body 114 to the inner wall of the front part of the tail beam skin 111;

[0144] S12. Make skin mounting holes on a local platform above the head of the tail beam skin 111 for subsequent connection of the first movable hinge 112 via fasteners.

[0145] The local platform design ensures that even with a large preload applied during the connection process, the skin will not experience concentrated stress points that could easily lead to damage.

[0146] S2. Prepare the tail beam quick-release body 121 of the tail beam quick-release assembly 12 in the tail beam component 1;

[0147] Install the tail beam connector 122, the left pin lock body 123, and the right pin lock body 124 on the outer bottom surface of the annular groove of the tail beam quick-release body 121.

[0148] Preferably, the tail beam connector 122 is riveted to the center of the upper part of the outer bottom surface of the annular groove of the tail beam quick-release body 121; the left pin lock body 123 and the right pin lock body 124 are symmetrically arranged along the middle part of the tail beam quick-release body 121 at the lower half of the outer bottom surface of the annular groove of the tail beam quick-release body 121, and are screwed together.

[0149] This symmetrical arrangement corresponds to the isosceles triangle formed by the first movable hinge 112 connecting to the local platform above the head of the tail beam skin 111, which is beneficial to the overall stress balance of the connection structure. More preferably, this triangle is arranged as an equilateral triangle.

[0150] S3. Install the quick-release tail beam body 121 onto the tail beam assembly 11;

[0151] S31. The first movable hinge body 1121, the tail beam skin 111 and the tail beam connector 122 are connected together by the first set of fasteners.

[0152] S32. Connect the left bolt lock body 123, the tail beam quick release body 121 and the left reinforcing body 113 together using the second set of fasteners.

[0153] S33. The right bolt lock body 124, the tail beam quick release body 121 and the right reinforcing body 114 are connected together by the second set of fasteners.

[0154] S34. Install bolt lock 32;

[0155] Install the two bolt locks 32 onto the left bolt lock body 123 and the right bolt lock body 124 respectively.

[0156] The connections made together in this step not only save space and fasteners, but are also an effective measure to reduce weight.

[0157] S4. Prepare fuselage docking frame 2;

[0158] S41. A left locking lock 23 and a right locking lock 24 are installed on the outer bottom surface of the annular groove of the docking frame 21, along with a protective body 25.

[0159] Preferably, the left locking 23 and the right locking 24 are symmetrically arranged along the middle of the docking frame 21 at the lower half of the outer bottom surface of the annular groove of the tail beam quick-release body 121, and correspond to the positions of the left pin lock body 123 and the right pin lock body 124, specifically by screw connection;

[0160] S42. Protective body 25 is installed on the outer bottom surface of the annular groove of the docking frame 21:

[0161] At the center of the lower part of the outer bottom surface of the quick-release body 121 of the tail beam, the protective body 25 is screwed on.

[0162] S43. Mounting holes are made on the upper part of the outer peripheral surface of the docking frame 21 for subsequent screwing of the second movable hinge body 221.

[0163] S5. Connect the fuselage docking frame 2 to the inner edge of the rear end of the fuselage body 100;

[0164] The docking frame 21 is inserted into the sleeve of the main body 100 from the rear end of the main body 100 with the groove facing forward, and is connected to the rear end of the main body 100. The outer plane of the bottom of the annular groove of the docking frame 21 is flush with the rear end of the main body 100. The outer circumferential surface of the docking frame 21 is riveted to the main body 100.

[0165] The outer plane of the bottom of the annular groove of the docking frame 21 is flush with the tail end of the fuselage body 100, which can ensure that the tail boom component 1 and the fuselage body 100 are connected without any overall seamless appearance, which is conducive to the good power of the unmanned helicopter.

[0166] S6. Using the quick-release tool component 3, the tail beam component 1 is quickly connected to the fuselage docking frame 2, thereby achieving a quick connection with the fuselage body 100.

[0167] S61. Push the head of the tail beam component 1 toward the main body 100, so that the outer end face of the protective body 25 contacts the outer bottom surface of the annular groove of the tail beam quick-release body 121; preferably, the height of the protective body 25 after height adjustment is slightly greater than the installation distance between the outer bottom surface of the annular groove of the tail beam quick-release body 121 and the outer bottom surface of the annular groove of the docking frame 21; this measure not only prevents accidental collision of the connecting parts, but also helps to increase the pre-tightening force and increase the stability of the connection structure.

[0168] S62, Connecting lock body locking structure;

[0169] At the same time, the left and right latch handles 321 are moved in opposite directions, so that the latch pin 322 enters the left latch hole 2311 and the right latch hole under the action of the latch return compression spring 323, and then the handles are released; thus forming a locking structure of the left and right lock bodies.

[0170] S63, Connect the movable hinge tool 31 to form the upper quick-release connecting hinge;

[0171] Align the second movable hinge hole 2211 and the first movable hinge hole 11211, install the movable hinge spring 312 and install two movable hinge handles 311 opposite to each other, and put the movable hinge handle posts of the two movable hinge handles 311 into the outer grooves of the radial slots of the first movable hinge adjustment groove 11212 respectively, and at the same time rotate the movable hinge handles to be parallel to the bottom plane of the first movable hinge body 1121; so that the first movable hinge body 1121 hinges to the second movable hinge body 221, forming an upper quick-release connecting hinge.

[0172] That is, the tail beam component 1 is quickly installed on the fuselage body 100.

[0173] Example 3

[0174] Figure 19 A method for quickly disassembling the tail boom of an unmanned helicopter is shown.

[0175] A method for quickly disassembling the locked tail boom of an unmanned helicopter includes the following steps:

[0176] T1. Move the connecting hinge tool 31 to separate the upper quick-release connecting hinge;

[0177] Rotate the two movable hinge handles 311 by 90° and compress the movable hinge spring 312. This will push the movable hinge handle post in the two movable hinge handles 311 into the inner groove of the radial slot of the first movable hinge adjustment groove 11212, causing the movable hinge insertion post to exit the second movable hinge hole 2211, thus separating the first movable hinge body 1121 from the second movable hinge body 221.

[0178] T2, Move the bolt lock 32 to separate the left and right lock body locking structures;

[0179] Simultaneously, turn the left bolt lock handle 321 clockwise and the right bolt lock handle 321 counterclockwise, so that the left and right bolt lock pins 322 simultaneously disengage from the left and right locking holes.

[0180] T3, separate the main fuselage 100 and the tail boom assembly 1;

[0181] Lift off the main body 100 or the tail beam component 1 to separate the two.

[0182] At this time, the tail beam quick-release assembly 12 is connected to the tail beam component 1; the fuselage docking frame 2 is connected to the fuselage body 100; this facilitates the quick installation and locking between the fuselage body 100 and the tail beam component 1 in the next operation.

[0183] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art outside the technical scope disclosed in the present invention should be included outside the scope of protection of the present invention. Furthermore, any equipment equipped with this device to expand its application field and produce combined technical effects falls within the scope of protection of this invention.

Claims

1. A quick installation and locking method of a tail boom of an unmanned helicopter, characterized in that, The unmanned helicopter tail beam comprises a tail beam component (1), a fuselage butt joint spacer frame component (2) and a quick release tool component (3); The tail beam component (1) comprises a tail beam assembly (11) and a tail beam quick release assembly (12), the tail beam assembly (11) comprises a tail beam skin (111), a left reinforcing body (113), a right reinforcing body (114) and a first movable hinge (112); The tail beam quick release assembly (12) comprises a tail beam quick release body (121) and a tail beam connecting unit, the tail beam connecting unit is connected to the tail beam quick release body (121); The left reinforcing body (113) and the right reinforcing body (114) are arranged inside the tail beam skin (111) of the shell as a support body and a connecting body, and can enhance the structural strength and connecting strength of the tail beam skin (111) at this position; The tail beam quick release body (121) is in a ring groove structure; the slot of the ring groove structure of the tail beam quick release body (121) is inserted into the barrel sleeve of the tail beam skin (111) from the front end of the tail beam skin (111) in the rear direction; the left reinforcing body (113) and the right reinforcing body (114) are inserted into the ring groove of the tail beam quick release body (121); the tail beam quick release body (121) is connected with the left reinforcing body (113) and the right reinforcing body (114) through a second set of fasteners, so that the tail beam quick release body (121) is connected with the tail beam skin (111) as a whole; the tail beam skin (111) can be connected with the fuselage main body (100) through the tail beam quick release body (121); The butt joint spacer frame (2) comprises a butt joint frame body (21) and a butt joint frame connecting assembly; the butt joint frame body (21) is in a ring groove structure; the butt joint frame connecting assembly comprises a second movable hinge (22), a left locking piece (23), a right locking piece (24) and a protection body (25); The quick release tool component comprises a movable hinge tool and a bolt lock; the quick release tool component is used for connecting the tail beam connecting unit and the butt joint frame connecting assembly, and forms a locking structure with the tail beam connecting unit and the butt joint frame connecting assembly; the tail beam connecting unit comprises a tail beam connecting body (122), a left bolt lock body and a right bolt lock body; the butt joint frame connecting assembly comprises a second movable hinge, a left locking piece and a right locking piece; the first movable hinge comprises a first movable hinge body; a first movable hinge position adjusting groove is arranged on the first movable hinge body; the movable hinge tool connects the first movable hinge and the second movable hinge, forms an upper quick release connecting hinge, and forms an upper quick release connecting hinge locking structure at the first movable hinge position adjusting groove; The quick installation and locking method comprises the following steps: S1, preparing the tail beam assembly (11) in the tail beam component (1); S2, preparing the tail beam quick release body (121) of the tail beam quick release assembly (12) in the tail beam component (1); S3, installing the tail beam quick release body (121) to the tail beam assembly (11); S4, preparing the fuselage butt joint spacer frame (2); S5, connecting the fuselage butt joint spacer frame (2) at the inner edge of the tail end of the fuselage main body (100); The docking frame (21) is inserted into the barrel sleeve of the fuselage body (100) from the tail end of the fuselage body (100) in the direction of the notch forward, and is connected at the tail end of the fuselage body (100), the outer plane of the ring groove bottom of the docking frame (21) is flush with the tail end of the fuselage body (100); S6, through the quick release tool component (3), the tail beam component (1) is quickly connected to the fuselage docking partition frame (2), and the quick connection with the fuselage body (100) is realized.

2. The quick installation locking method of the unmanned helicopter tail beam according to claim 1, characterized in that, S1 includes connecting the first movable hinge (112), the left reinforcing body (113) and the right reinforcing body (114) to the tail beam skin (111).

3. The quick installation locking method of the unmanned helicopter tail beam according to claim 2, characterized in that, In S2, the outer peripheral side surface of the ring groove structure of the tail beam quick release body (121) is shaped as a whole on the inner side surface of the head of the tail beam skin (111), and is arranged with a gap at the inner side surface of the head of the tail beam skin (111).

4. The quick installation locking method of the unmanned helicopter tail beam according to claim 3, characterized in that, S2 includes installing the tail beam connecting body (122) on the ring groove structure outer peripheral side surface platform of the tail beam quick release body (121), and connecting the left bolt lock body (123) and the right bolt lock body (124) on the ring groove bottom outer surface of the tail beam quick release body (121).

5. The quick installation locking method of the unmanned helicopter tail beam according to claim 4, characterized in that, S3 includes installing the tail beam quick release body (121) to the tail beam assembly (11) through the first group of fasteners and the second group of fasteners.

6. The quick installation locking method of the unmanned helicopter tail beam according to claim 5, characterized in that, In S4, the outer peripheral side surface of the docking frame (21) is shaped as a whole on the inner side surface at the tail end of the fuselage body (100); S4 includes connecting the second movable hinge (22), the left locking (23), the right locking (24) and the protection body (25) to the docking frame (21).

7. The quick installation locking method of the unmanned helicopter tail beam according to claim 6, characterized in that, S5 includes aligning the ring groove bottom outer surface of the docking frame (21) with the tail end of the fuselage body (100), and connecting at the tail end of the fuselage body (100).

8. The quick installation locking method of the unmanned helicopter tail beam according to claim 7, characterized in that, S6 includes connecting the two bolt locks (32) to the left locking (23) and the right locking (24) respectively, and installing the movable hinge tool (31) at the hinge joint of the first movable hinge (112) and the second movable hinge (22).

9. The quick installation locking method of the unmanned helicopter tail beam according to claim 7, characterized in that, S6 includes actuating the movable hinge tool (31) to form an upper quick release connection hinge lock, and actuating the two bolt locks (32) to form a left and right two lock body locking structure.

10. A method of quick release of a tail boom of an unmanned helicopter, characterized in that, The unmanned helicopter tail beam mounted on the tail end of the fuselage body (100) is quickly disassembled, including the following steps: The unmanned helicopter tail beam includes a tail beam component (1), a fuselage docking partition frame component (2) and a quick release tool component (3); The tail beam component (1) includes a tail beam assembly (11) and a tail beam quick release assembly (12), the tail beam assembly (11) includes a tail beam skin (111), a left reinforcing body (113), a right reinforcing body (114) and a first movable hinge (112); The tail beam quick release assembly (12) includes a tail beam quick release body (121) and a tail beam connecting unit, the tail beam connecting unit is connected to the tail beam quick release body (121); The left reinforcing body (113) and the right reinforcing body (114) are used as supporting bodies and connecting bodies, are arranged on the inner side of the tail beam skin (111) of the shell, and can enhance the structural strength and connecting strength of the tail beam skin (111) at this position; The tail beam quick release body (121) is a ring groove structure; the notch of the ring groove structure of the tail beam quick release body (121) is inserted into the tail beam skin (111) sleeve from the front end of the tail beam skin (111) in the rear direction; the left reinforcing body (113) and the right reinforcing body (114) are inserted into the ring groove of the tail beam quick release body (121); the tail beam quick release body (121) is connected with the left reinforcing body (113) and the right reinforcing body (114) through the second group of fasteners, so that the tail beam quick release body (121) is connected with the tail beam skin (111) as a whole; the tail beam skin (111) can be connected with the fuselage main body (100) through the tail beam quick release body (121); The docking partition frame (2) comprises a docking frame body (21) and a docking frame connecting assembly; the docking frame body (21) is a ring groove structure; the docking frame connecting assembly comprises a second movable hinge (22), a left locking piece (23), a right locking piece (24) and a protection body (25); The quick release tool component comprises a movable hinge tool (31) and a bolt lock; the quick release tool component is used for connecting the tail beam connecting unit and the docking frame connecting assembly, and forms a locking structure with the tail beam connecting unit and the docking frame connecting assembly; the tail beam connecting unit comprises a tail beam connecting body 122, a left bolt lock body and a right bolt lock body; the docking frame connecting assembly comprises a second movable hinge, a left locking piece and a right locking piece; the first movable hinge comprises a first movable hinge body; a first movable hinge adjusting groove is arranged on the first movable hinge body; the movable hinge tool connects the first movable hinge and the second movable hinge, forms an upper quick release connecting hinge, and forms an upper quick release connecting hinge locking structure at the first movable hinge adjusting groove; T1, move the connecting movable hinge tool (31) to separate the upper quick release connecting hinge; T2, move the bolt lock (32) to separate the left and right lock body locking structures; T3, separate the fuselage main body (100) and the tail beam component (1).

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