Plug-in type assembled airframe structure and unmanned aerial vehicle

Abstract

The invention relates to an airframe structure assembled in a plug-in mode and an unmanned aerial vehicle, the airframe structure assembled in a plug-in mode comprises an airframe main body, a side arm, an undercarriage and a load turnover mechanism, the side arm is connected with the airframe main body, the undercarriage is installed on the side arm, the load turnover mechanism is installed below the airframe main body, and the load turnover mechanism is connected with the side arm. When the side arms are in the storage state, the undercarriage is also in the storage state; when the side arms are unfolded, the undercarriage is automatically unfolded and locked; the load turnover mechanism can be stored below the main machine arm in front of the machine body. The foldable unmanned aerial vehicle body structure is simple and compact in structure, easy and convenient to operate and convenient to store and transport; the method can be applied to multi-rotor unmanned aerial vehicle air launching projects; the machine body structure is processed and formed by adopting a standard plate and pipe composite material without customizing a mold for processing and production.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a plug-in assembled airframe structure and an unmanned aerial vehicle. Background Art

[0002] With the development of unmanned aerial vehicle technology, there are also higher and higher requirements for the production cost and airframe structure of unmanned aerial vehicles. There are various types of existing unmanned aerial vehicles, including foldable arms and non-foldable arms. Since the structure of unmanned aerial vehicles with foldable arms has the advantages of high space utilization rate, small storage space, convenience in transportation, flexible cooperation with the air launch mode, and reduction of the range requirement of unmanned aerial vehicles, it is widely used in various industries at present. However, most of the current airframe structures of unmanned aerial vehicles require mold opening, and a separate mold needs to be developed for each model or specification, and it can only be achieved through multiple tests and debugging. Therefore, it has the disadvantages of high production cost, long production cycle, and difficult debugging. There is an urgent need to develop a plug-in airframe structure suitable for multi-rotor unmanned aerial vehicles. Summary of the Invention

[0003] In order to overcome the problems existing in the prior art, the present invention provides a plug-in assembled airframe structure and an unmanned aerial vehicle to overcome the current defects.

[0004] A plug-in assembled airframe structure for an unmanned aerial vehicle, the structure comprising: a fuselage main body, side arms, landing gears, and a payload flipping mechanism. The side arms are connected to the fuselage main body, the landing gears are installed on the side arms, and the payload flipping mechanism is installed under the fuselage main body. Wherein, when the side arms are in the stowed state, the landing gear rods are also in the stowed state; when the side arms are deployed, the landing gears automatically deploy and lock; the payload flipping mechanism can be stowed under the front main arm of the fuselage.

[0005] In the above aspect and any possible implementation manner, a further implementation manner is provided, wherein the fuselage main body includes a fuselage frame beam and a fuselage frame plate, and the two are connected by mortise and tenon joints.

[0006] In the above aspect and any possible implementation manner, a further implementation manner is provided, wherein the side arms are located on both sides of the fuselage main body and include side arm shafts, side arm shaft ends, side arm plates, side arm C-shaped reinforcing frames, side arm tubes, power system mounting seats, rib plates, pipe clamps, and locking mechanisms.

[0007] In the above aspect and any possible implementation manner, a further implementation manner is provided, wherein the landing gears are located under the side arms and include landing gear rods, landing gear bases, and tensioning devices.

[0008] For the aspects and any possible implementation manners described above, a further implementation manner is provided. The payload flipping mechanism is located below the fuselage main body and includes a servo, a servo base, a payload plate, wheels, bearings, and a rotating shaft.

[0009] For the aspects and any possible implementation manners described above, a further implementation manner is provided. The fuselage frame beam includes a cross beam, an upper longitudinal beam, an intermediate upper longitudinal beam, a lower longitudinal beam, an intermediate lower longitudinal beam, and side bars.

[0010] For the aspects and any possible implementation manners described above, a further implementation manner is provided. The fuselage frame plate includes a front upper fuselage plate, a front arm frame plate, front and rear side wall plates of the fuselage, a servo base mounting plate, side wall plates of the fuselage, a transverse arm support plate, a lower frame plate of the fuselage, a small front upper plate of the fuselage, a rear arm frame plate, a front frame plate of the fuselage, an upper frame plate of the fuselage, a rear frame plate of the fuselage, a small rear upper plate of the fuselage, a front frame plate of the rear arm, a rear upper plate of the fuselage, side bars, rear side wall plates of the fuselage, a small rear lower plate of the fuselage, and a rear lower plate of the fuselage.

[0011] For the aspects and any possible implementation manners described above, a further implementation manner is provided. It further includes a main arm strengthening frame, which is installed on the outer side of the main arm and fixed on the front upper fuselage plate to strengthen the main arm.

[0012] For the aspects and any possible implementation manners described above, a further implementation manner is provided. It further includes long pipe clamps and pipe clamp covers for connecting the main arm and the fuselage main body.

[0013] The present invention also provides a drone, and the drone includes the structure described above.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] The present invention has the following advantages compared with the prior art:

[0016] (1) During the processing and manufacturing of the fuselage structure of the present invention, there is no need to separately open a mold. The fuselage structure has a light self-weight, high strength, low cost, short processing cycle, and strong practicability.

[0017] (2) Before the side arms of the present invention are deployed, they are parallel to the fuselage, reducing the volume in the storage state. After deployment, there is anhedral, which can increase the stability of the aircraft during flight.

[0018] (3) The present invention is designed with a payload flipping mechanism, which can observe the surrounding environment without obstruction in all directions during the hovering and flight of the aircraft after the payload is deployed.

[0019] (4) The landing gear automatic deployment mechanism of the present invention has a simple principle, low cost, and strong reliability. Description of the Drawings

[0020] Figure 1 This is a schematic diagram of the structure of the whole machine in the deployed working state of the present invention.

[0021] Figure 2 This is a schematic diagram of the structure of the whole machine in the stored state of the present invention.

[0022] Figure 3 This is a schematic diagram of the main body structure of the fuselage of the present invention.

[0023] Figure 4 This is a schematic diagram of the installation relationship between the main arm and the main body structure of the fuselage of the present invention.

[0024] Figure 5 This is a schematic diagram of the side arm structure of the present invention.

[0025] Figure 6 This is a schematic diagram of the payload stored state of the present invention.

[0026] Figure 7 This is a schematic diagram of the payload deployed state of the present invention.

[0027] Figure 8 This is a schematic diagram of the landing gear stored state of the present invention. Detailed implementation manners

[0028] In order to better understand the technical solution of the present invention, the content of the present invention includes but is not limited to the following detailed implementation manners. Similar technologies and methods should be regarded as within the scope of protection of the present invention. To make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following will be described in detail with reference to the drawings and specific embodiments.

[0029] It should be clear that the embodiments described in the present invention are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present invention without creative efforts belong to the scope of protection of the present invention.

[0030] The plug-in assembled airframe structure of the present invention is used for an unmanned aerial vehicle. The structure includes: a fuselage main body, side arms, landing gears, and a payload flipping mechanism. The side arms are connected to the fuselage main body. The landing gears are installed on the side arms. The payload flipping mechanism is installed below the fuselage main body. Wherein, when the side arms are in the stowed state, the landing gear rods are also in the stowed state; when the side arms are deployed, the landing gears are automatically deployed and locked; the payload flipping mechanism can be stowed below the front main arm of the fuselage. The airframe structure of the present invention is a foldable unmanned aerial vehicle airframe structure that is simple and compact, easy to operate, and convenient for storage and transportation; it can be applied to multi-rotor unmanned aerial vehicle air launch projects; the airframe structure is processed and formed by using standard sheet materials and pipe materials composite materials, without custom mold processing and production. For the normal operation and use of the unmanned aerial vehicle during storage, transportation, and flight, the technology is mature and reliable, which can reduce the production cost and processing cycle of the unmanned aerial vehicle.

[0031] As Figure 1 shown, the airframe structure of the embodiment of the present invention includes a main arm 1, a payload flipping mechanism 2, a fuselage main body 3, side arms 4, and landing gears 5. Among them, the side arms 4 are connected to the fuselage main body 3 through arm shafts. The landing gears 5 are installed on the side arms 4. The payload flipping mechanism 2 is installed below the fuselage main body 3. Among them, the main arm 1 and the side arms 4 serve as carriers for motors and propellers, and are used to fix the motors and propellers and transmit their power to the entire fuselage. The payload flipping mechanism 2 is used to install and adapt mission payloads with different interface sizes, and at the same time control the switching of the payload between the stowed and deployed states. The fuselage main body 3 is the basic structure of the entire fuselage, and bears the airframe structures such as the unmanned aerial vehicle payload flipping mechanism 2, the main arm 1, and the side arms 4, as well as electrical structures such as energy, power, and control circuits. The landing gears 5 are used to bear the fuselage when the unmanned aerial vehicle takes off and lands.

[0032] Furthermore, the fuselage main body 3 is composed of standard sheet materials and pipe materials and other composite materials. This material is a shelf product, which can be directly purchased to shorten the production cycle, has low cost, stable and reliable quality, and good product consistency. As Figure 3 shown, the fuselage main body structure includes a fuselage frame beam and a fuselage frame plate. The fuselage frame beam is used to support the fuselage frame plate, serves as the overall fuselage skeleton, and bears the acting forces of various parts of the fuselage. The fuselage frame plate is used to determine the positions of the various fuselage frame beams and fix the on-board equipment.

[0033] Among them, the fuselage frame beam is composed of twenty cross beams 6, two upper longitudinal beams 7, one middle upper longitudinal beam 8, two lower longitudinal beams 10, one middle lower longitudinal beam 14, and four side rods 26. The cross beams 6 are respectively located between the upper longitudinal beam 7 and the middle upper longitudinal beam 8, and between the lower longitudinal beam 10 and the middle lower longitudinal beam 14 for positioning and connecting the respective upper and lower longitudinal beams, and at the same time bearing the lateral acting forces of the fuselage.

[0034] The upper longitudinal beam 7 and the middle upper longitudinal beam 8 are located at the upper part of the fuselage frame beam. The two upper longitudinal beams 7 are symmetrically distributed on both sides of the middle upper longitudinal beam 8 to bear the longitudinal force of the fuselage and form the upper fuselage frame beam with the cross beam 6.

[0035] The lower longitudinal beam 10 and the middle lower longitudinal beam 14 are located at the lower part of the fuselage frame beam. The two lower longitudinal beams 10 are symmetrically distributed on both sides of the middle lower longitudinal beam 14 to bear the longitudinal force of the fuselage and form the lower fuselage frame beam with the cross beam 6.

[0036] The side rod 26 is located between the upper longitudinal beam 7 and the lower longitudinal beam 10, and is used to connect the upper and lower fuselage frame beams.

[0037] The fuselage frame is composed of the upper front panel 9, the front frame panel of the arm 11, the front and rear side wall panels 12 of the fuselage, the steering gear seat mounting plate 13, the side wall panel 15 of the fuselage, the arm support horizontal panel 16, the lower frame panel 17 of the fuselage, the front small panel 18 of the fuselage, the rear frame panel 19 of the arm, the front frame panel 20 of the fuselage, the upper frame panel 21 of the fuselage, the rear frame panel 22 of the fuselage, the rear small panel 23 of the fuselage, the front frame panel 24 of the rear arm, the upper and rear panels 25 of the fuselage, the rear side wall panel 27 of the fuselage, the lower rear small panel 28 of the fuselage and the lower rear panel 29 of the fuselage. The upper front panel 9 is located in front of the fuselage and below the upper longitudinal beam 7, plugged with the front frame panel 11 of the arm, and bonded with the upper longitudinal beam 7, and is used to carry the fuselage equipment.

[0038] The front frame plate 11 of the arm is located behind the front plate 9 of the fuselage, and is interspersed with the upper longitudinal beam 7, the middle upper longitudinal beam 8, and the lower longitudinal beam 10, and is plugged with the front plate 9 of the fuselage, the front and rear side wall plates 12 of the fuselage, the front small plate 18 of the fuselage, and the steering gear seat mounting plate 13 to reinforce the fuselage.

[0039] There are four front and rear side wall panels 12 of the fuselage, two of which are located in the front of the fuselage and plugged into the front frame panel 11 of the arm to increase the deflection and strength of the front frame panel 11 of the arm, and two of which are located in the rear of the fuselage and plugged into the rear front frame panel 24 of the rear arm to increase the deflection and strength of the rear front frame panel 24 of the arm.

[0040] The steering gear seat mounting plate 13 is located in front of the fuselage and above the lower longitudinal beam 7, and is plugged with the arm front frame plate 11, the arm rear frame plate 19, the fuselage side wall plate 15, and the fuselage front frame plate 20 for installing the steering gear seat.

[0041] The fuselage side wall plate 15 is located on both sides of the upper longitudinal beam 7 and the lower longitudinal beam 10, and is plugged with the arm rear frame plate 19, the fuselage front frame plate 20, the arm support cross plate 16, the fuselage front small plate 18, the steering gear seat mounting plate 13, the fuselage upper frame plate 21, and the fuselage lower frame plate 17 to reinforce the fuselage.

[0042] The arm support transverse plate 16 is located in front of the fuselage, and is plugged with the arm rear frame plate 19, the fuselage front frame plate 20, and the fuselage side wall plate 15 to reinforce the arm.

[0043] The lower frame plate 17 of the fuselage is located in the middle of the fuselage, above the lower longitudinal beam 7 and the middle lower longitudinal beam 8, and is bonded to the lower longitudinal beam 10 and the middle lower longitudinal beam 14 for installing fuselage equipment.

[0044] The front small plate 18 of the fuselage is located behind the front plate 9 of the fuselage and below the upper longitudinal beam 7, and is inserted into the front frame plate 11 of the arm, the rear frame plate 19 of the arm, the front frame plate 20 of the fuselage, and the side wall plate 15 of the fuselage, and is bonded to the upper longitudinal beam 8 for carrying fuselage equipment.

[0045] The rear frame plate 19 of the arm is parallel to the front frame plate 11 of the arm, located behind the front frame plate 11 of the arm, and is intersected with the upper longitudinal beam 7, the middle upper longitudinal beam 8, and the lower longitudinal beam 10, and is inserted into the front small plate 18 of the fuselage, the side wall plate 15 of the fuselage, the support cross plate 16 of the arm, and the mounting plate 13 of the servo base for strengthening the fuselage.

[0046] The front frame plate 20 of the fuselage is parallel to the front frame plate 11 of the arm, located behind the rear frame plate 19 of the arm, and is intersected with the upper longitudinal beam 7, the middle upper longitudinal beam 8, the lower longitudinal beam 10, and the middle lower longitudinal beam 14, and is inserted into the front small plate 18 of the fuselage, the side wall plate 15 of the fuselage, the support cross plate 16 of the arm, and the mounting plate 13 of the servo base for strengthening the fuselage.

[0047] The upper frame plate 21 of the fuselage is located in the middle of the fuselage, above the upper longitudinal beam 7 and the middle upper longitudinal beam 8, and is bonded to the upper longitudinal beam 7 and the middle upper longitudinal beam 8 for installing fuselage equipment.

[0048] The rear frame plate 22 of the fuselage is parallel to the front frame plate 11 of the arm, located at the rear of the fuselage, and is intersected with the upper longitudinal beam 7, the middle upper longitudinal beam 8, the lower longitudinal beam 10, and the middle lower longitudinal beam 14, and is inserted into the rear small plate 23 of the fuselage, the rear side wall plate 27 of the fuselage, and the lower rear small plate 28 of the fuselage for strengthening the fuselage.

[0049] The rear small plate 23 of the fuselage is located behind the rear frame plate 22 of the fuselage and below the upper longitudinal beam 7, and is inserted into the rear frame plate 22 of the fuselage, the front frame plate 24 of the rear arm, and the rear side wall plate 27 of the fuselage, and is bonded to the upper longitudinal beam 7 for carrying fuselage equipment.

[0050] The front frame plate 24 of the rear arm is parallel to the front frame plate 11 of the arm, located behind the rear frame plate 22 of the fuselage, and is intersected with the upper longitudinal beam 7, the middle upper longitudinal beam 8, and the lower longitudinal beam 14, and is inserted into the rear small plate 23 of the fuselage, the rear plate 25 of the fuselage, the lower rear plate 29 of the fuselage, and the front and rear side wall plates 12 of the fuselage for carrying fuselage equipment.

[0051] The rear plate 25 of the fuselage is located behind the rear small plate 23 of the fuselage and below the upper longitudinal beam 7, and is inserted into the front frame plate 24 of the rear arm and the front and rear side wall plates 12 of the fuselage for carrying fuselage equipment.

[0052] The rear side wall panel 27 of the fuselage is located on both sides of the upper longitudinal beam 7 and the lower longitudinal beam 14, and is inserted into the rear frame panel 22, the upper rear small panel 23, the lower rear small panel 28, the upper frame panel 21, and the lower frame panel 17 of the fuselage to reinforce the fuselage.

[0053] The lower rear small panel 28 of the fuselage is located behind the rear frame panel 22 of the fuselage and above the lower longitudinal beam 14, and is inserted into the rear frame panel 22, the rear side wall panel 27 of the fuselage, and the front and rear side wall panels 12 of the fuselage, and is bonded to the lower longitudinal beam 14 for carrying the fuselage equipment.

[0054] The lower rear panel 29 of the fuselage is located behind the lower rear small panel 28 of the fuselage and above the lower longitudinal beam 14, and is inserted into the front frame panel 24 of the rear arm and the front and rear side wall panels 12 of the fuselage, and is bonded to the lower longitudinal beam 14 for carrying the fuselage equipment.

[0055] The parts between the fuselage frame beams and the fuselage frame panels are inserted in a mortise and tenon manner, and are fixed at the interfaces using a wet bonding process.

[0056] As Figure 2 shown, it is a schematic structural diagram of the whole machine in the stored state. In this state, the side arm 4 rotates to be parallel to the main arm 1, the landing gear 5 is pulled out from the landing gear seat and placed above the servo seat mounting plate 13 and the lower rear panel 29 of the fuselage, and the load flipping mechanism 2 drives the load to rotate below the front main arm 1 of the fuselage.

[0057] As Figure 4 shown, the main arm 1 is fixed to the fuselage main body 3 through the long pipe clamp 31 and the pipe clamp cover 32. There are pin holes in the main arm 1 and the long pipe clamp 31, and they are positioned by the positioning pin to prevent the main arm from rotating around the axis. The main arm reinforcement frame 33 is of a C-shaped structure and is installed on the outside of the main arm 1 and fixed to the upper front panel 9 of the fuselage to strengthen the structure of the main arm.

[0058] As Figure 6 shown, the load flipping mechanism 2 includes a servo seat 45, a servo cover 46, a servo 47, a load adapter plate 48, and a load 49. Among them, the servo seat 45 is installed on the middle lower longitudinal beam 14 and the lower frame panel 17 of the fuselage to fix the servo 47. The servo cover 46 is fixed to the servo seat to strengthen the fixation of the servo 47 by the fuselage. One side of the load adapter plate 48 is fixed to the servo disc (not shown in the figure), and the other side is fixed to the servo seat 45 through a rotating shaft and a bearing. The load adapter plate 48 is provided with two mechanical limits, which are located at the starting and ending positions of the stroke respectively to protect the servo 47. The load 49 is installed on the load adapter plate 48, and the load adapter plate 48 can be adapted to a variety of loads.

[0059] When the load 49 is in the stored state, the servo can drive the load adapter plate and the load to be stored below the front main arm 1 of the fuselage. As Figure 7As shown, when the payload is in the deployed state, it can be flipped under the fuselage, enabling the UAV to observe the surrounding environment omni-directionally without obstruction.

[0060] As Figure 5 shown, the side arm 4 consists of a shaft cover 34, a shaft screw 35, an arm bearing 36, a carbon tube support 37, a side arm shaft end 38, a copper sleeve 39, a shaft seat 40, a side arm shaft 41, a side arm plate 42, a side arm reinforcement frame 43, and a side arm tube 44.

[0061] The shaft cover 34 is located above the upper longitudinal beam 7 and is connected to the shaft seat 40 and the upper longitudinal beam 7 for fixing the arm bearing 36; the shaft screw 35 is located inside the shaft cover 34 and passes through the shaft cover 34, the arm bearing 36, the upper longitudinal beam 7, the carbon tube support 37, the shaft seat 40 to be connected to the side arm shaft end 38 for adjusting the up and down position of the side arm 4; the arm bearing 36 is located inside the shaft cover 34 and is fixed by the shaft screw 35 to facilitate the rotation of the side arm 4; the carbon tube support 37 is located inside the upper longitudinal beam 7 for strengthening the structural strength at the rotation axis; the side arm shaft end 38 is located at both ends of the side arm plate 42 for positioning and rotating the side arm 4; the copper sleeve 39 is located inside the shaft seat 40 for rotational lubrication of the side arm shaft end 38; the shaft seat 40 is located below the upper longitudinal beam 7 and is connected to the shaft cover 34 and the upper longitudinal beam 8 for positioning and installing the side arm 4; the side arm shaft 41 is located on the side arm plate 42 for fixing the side arm shaft end 38; the side arm plate 42 is located at the end of the arm for strengthening the side arm 4; the side arm reinforcement frame 43 is located on both sides of the side arm plate 42 for strengthening the side arm 4; the side arm tube 44 is the main structure of the side arm 4 for carrying the power device of the UAV and transmitting power.

[0062] Among them, the side arm shaft 41 has a certain angle with the Z coordinate axis of the fuselage. As Figure 5 shown, when the side arm is in the stowed state, the axis of the side arm tube 44 is parallel to the X coordinate axis of the fuselage. The side arm has anhedral (there is an angle between the axis of the side arm tube and the XY plane of the fuselage ( Figure 1 the plane determined by the X and Y axes in the coordinate system)), which increases the flight stability of the UAV. Among them, the length direction of the fuselage is the X-axis direction, the direction perpendicular to the length direction of the fuselage and in the same plane is used as the Y-axis direction, and the direction perpendicular to the plane where the X and Y axes are located is the Z-axis direction, that is, the Z coordinate axis.

[0063] As Figure 8As shown in the figure, the landing gear 5 is located below the side arm 4, and includes a landing gear rod 53, a landing gear base 54, a rubber pad mounting seat 52, a rubber pad 51, and a tensioning device 55. Among them, the landing gear rod 53 is located below the landing gear base 54 and is used to support the takeoff and landing of the drone; the landing gear base 54 is located below the side arm 4 and is used to fix the landing gear rod 53; the rubber pad mounting seat 52 is located at the end of the landing gear rod 53 and is used to fix the rubber pad 51 and the tensioning device 55; the rubber pad 51 is located below the rubber pad mounting seat 52 and is used for anti-slip and vibration reduction; one end of the tensioning device 55 passes through the landing gear rod 53 and is fixed to the rubber pad mounting seat 52, and the other end is fixed to the side arm 4 and is used to restore the landing gear 5 to the deployed state during the deployment process of the landing gear 5.

[0064] When the side arm 4 is in the stowed state, the landing gear rod 53 is also in the stowed state. When the side arm 4 is deployed, the landing gear 5 is automatically deployed and locked under the influence of gravity and the tensioning device 55 at the end of the landing gear rod.

[0065] As an embodiment disclosed in the present invention, the present invention also provides a drone, and the drone includes the structure described in the present invention.

[0066] The terms used in the embodiments of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The singular forms "a", "the", and "said" used in the embodiments of the present invention and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise.

[0067] The above description shows and describes several preferred embodiments of the present invention. However, as mentioned above, it should be understood that the present invention is not limited to the forms disclosed herein, should not be regarded as excluding other embodiments, but can be used in various other combinations, modifications and environments, and can be within the scope of the application concept described herein, through the above teachings or the technology or knowledge in related fields. And the changes and modifications made by those skilled in the art that do not depart from the spirit and scope of the present invention should all be within the protection scope of the appended claims of the present invention.

Claims

1. A plug-in assembly body structure for a drone, characterized in that: The structure includes: a fuselage body, a side arm, a landing gear, and a load-turning mechanism, wherein the side arm is connected to the fuselage body, the landing gear is mounted on the side arm, and the load-turning mechanism is mounted below the fuselage body, wherein when the side arm is in a stowed state, the landing gear is also in a stowed state; when the side arm is deployed, the landing gear is automatically deployed and locked; the load-turning mechanism can be stored below the front main arm of the fuselage.

2. The plug-in assembly body structure according to claim 1, characterized in that: The fuselage body comprises a fuselage frame beam and a fuselage frame plate, which are connected by mortise and tenon joints.

3. The plug-in assembly body structure according to claim 1, characterized in that: The side arms are located on both sides of the fuselage body, and include side arm shafts, side arm shaft ends, side arm plates, side arm C-shaped reinforcement frames, side arm tubes, power system mounting seats, rib plates, pipe clamps and locking mechanisms.

4. The plug-in assembly body structure according to claim 1, characterized in that: The landing gear is located below the side arm and comprises a landing gear rod, a landing gear base and a tensioning device.

5. The plug-in assembly body structure according to claim 1, characterized in that: The load turnover mechanism is located below the fuselage body, and comprises a steering gear, a steering gear seat, a load plate, a wheel, a bearing and a rotating shaft.

6. The plug-in assembly body structure according to claim 2, characterized in that: The fuselage frame beam comprises a cross beam, an upper longitudinal beam, an intermediate upper longitudinal beam, a lower longitudinal beam, an intermediate lower longitudinal beam and a side rod.

7. The plug-in assembly body structure according to claim 2, characterized in that: The fuselage frame panels include an upper front panel on the fuselage, an arm front frame panel, front and rear side wall panels on the fuselage, a steering gear seat mounting panel, a fuselage side wall panel, an arm supporting cross panel, a fuselage lower frame panel, a fuselage front small panel, an arm rear frame panel, a fuselage front frame panel, a fuselage upper panel, a fuselage rear frame panel, a fuselage rear small panel, a rear arm front frame panel, a fuselage upper and rear panels, a side rod, a fuselage rear side wall panel, a fuselage lower rear small panel and a fuselage lower rear panel.

8. The plug-in assembly body structure according to claim 7, characterized in that: It also includes a host arm reinforcement frame, which is installed on the outside of the host arm and fixed on the front plate of the fuselage to strengthen the host arm.

9. The plug-in assembly body structure according to claim 1, characterized in that: It also includes a long pipe clamp and a pipe clamp cover for connecting the mainframe arm and the fuselage body.

10. A drone, characterized in that: The drone comprises the structure described in any one of claims 1-9.

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