Unmanned aerial vehicle shell and unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle shell and an unmanned aerial vehicle. The unmanned aerial vehicle shell comprises a carbon-based shell, a carbon-based top cover and an aluminum reinforcing frame. A battery bin is arranged in the carbon-based shell, and an opening is formed in the position, located on the carbon-based shell, of the battery bin. The position, corresponding to the opening, of the carbon-based top cover is in butt joint with the carbon-based shell, and the carbon-based top cover is configured to be capable of making contact with the battery assembled in the battery bin. The aluminum reinforcing frame is arranged between the carbon-based shell and the carbon-based top cover, and the carbon-based top cover and the carbon-based shell are in butt joint to form an integrated machine shell of a carbon-clamped aluminum structure. According to the unmanned aerial vehicle shell, the carbon-clamped aluminum structure is utilized, so that the unmanned aerial vehicle shell has good bending resistance, compression resistance and heat dissipation performance, and the stability of the structure is kept while the unmanned aerial vehicle shell bears a large load.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV casing and a UAV. Background Technology

[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aircraft controlled by radio remote control equipment and their own program control devices, or operated autonomously, either completely or intermittently, by an onboard computer. UAVs can be categorized into military and civilian applications. In the military field, UAVs are divided into reconnaissance aircraft and target drones. In the civilian field, they are currently widely used in aerial photography, agriculture, plant protection, miniature selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying, news reporting, power line inspection, disaster relief, film and television production, and creating romantic scenes, greatly expanding the uses of UAVs.

[0003] During flight, drones frequently encounter impacts due to complex terrain or environments. Current drone casings have relatively low structural strength and lack effective impact absorption, easily damaging internal electronic components. Furthermore, the heat generated during drone operation can lead to heat buildup in enclosed casings, affecting the drone's performance and lifespan. Utility Model Content

[0004] The purpose of this utility model is to provide a drone housing and a drone to solve the problems of low structural strength and poor heat dissipation of drone housings in the prior art.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] This utility model discloses a drone casing, including a carbon-based outer shell, a carbon-based top cover, and an aluminum reinforcing frame. A battery compartment is disposed inside the carbon-based outer shell, and the battery compartment has an opening on the carbon-based outer shell. The carbon-based top cover is aligned with the carbon-based outer shell at the position corresponding to the opening, and the carbon-based top cover is configured to contact the battery assembled in the battery compartment. The aluminum reinforcing frame is disposed between the carbon-based outer shell and the carbon-based top cover, and the carbon-based top cover and the carbon-based outer shell, when aligned, form an integrated casing with a carbon-aluminum structure.

[0007] Optionally, the aluminum reinforcing frame is placed flat on the opening of the carbon-based shell, and the aluminum reinforcing frame has an annular structure corresponding to the opening. The carbon-based top cover includes a cover plate and a support boss disposed on the bottom surface of the cover plate and engaging with the opening. After the carbon-based top cover and the carbon-based shell are engaged, the aluminum reinforcing frame fits onto the side wall of the support boss and provides support between the opening of the carbon-based shell and the cover plate.

[0008] Optionally, the aluminum reinforcing frame is provided with an extension frame located outside the carbon-based outer shell, so that the extension frame can be used for accessory installation.

[0009] Optionally, the extension frame includes a first horizontal plate, a second horizontal plate, and a vertical plate. The first horizontal plate is integrally formed with the outer ring wall of the aluminum reinforcing frame. The vertical plate connects the first horizontal plate and the second horizontal plate, and the extension frame forms a "Z" shaped structure. The second horizontal plate has a plurality of assembly holes.

[0010] Optionally, a carbon-based partition plate is provided inside the carbon-based shell, which divides the internal space of the carbon-based shell into the battery compartment located above and the control compartment located below. The battery compartment has space for stacking and laying batteries flat, and the compartment structure is configured to correspond to the battery structure. The control compartment is used to arrange control circuit boards.

[0011] Optionally, the carbon-based partition plate is fitted inside the carbon-based outer shell, and a set of opposite sidewalls of the carbon-based partition plate form a wire-passing gap with the inner wall of the carbon-based outer shell. The carbon-based partition plate is provided with a plurality of first fixing holes, and the bottom surface of the control compartment is provided with a plurality of second fixing holes corresponding one-to-one with the first fixing holes. Connecting bolts are provided between the first fixing holes and the corresponding second fixing holes.

[0012] Optionally, the battery compartment wall is provided with a plurality of heat dissipation holes penetrating the carbon-based outer shell, and the battery compartment is provided with a first heat dissipation fin for separating the battery compartment and the battery, and / or a second heat dissipation fin for separating the battery and adjacent batteries.

[0013] Optionally, the carbon-based outer shell is provided with carbon-based wing rods distributed in four directions. One end of the carbon-based wing rod is integrally formed with the outer wall of the carbon-based outer shell, and the other end of the carbon-based wing rod is provided with a carbon-based mounting base so that the carbon-based mounting base can be used for mounting the flight propeller.

[0014] This utility model also discloses a drone, including the drone shell described above, a battery assembly disposed in the battery compartment, an electronic control assembly disposed in the drone shell, and a flight assembly disposed on the drone shell;

[0015] The battery assembly includes multiple battery cells laid flat in the battery compartment. Each battery cell includes multiple individual battery cells stacked and connected in series to form a battery pack. The battery compartment is provided with a main power port that connects the multiple laid-flat battery cells in parallel.

[0016] The electronic control assembly includes a flight control board and a power distribution board laid flat. The power distribution board is electrically connected to the main power port and the flight control board, respectively, and is also electrically connected to the flight assembly.

[0017] Optionally, the flight assembly includes a drive motor and a propeller connected to the output end of the drive motor. The flight assembly is distributed in four directions on the UAV casing, and the four drive motors are electrically connected to the power distribution board.

[0018] Compared with the prior art, the beneficial effects of the drone casing and drone provided by this utility model embodiment are as follows:

[0019] By incorporating a carbon-based outer shell, a carbon-based top cover, and an aluminum reinforcing frame, the main body of the drone's casing is formed by the carbon-based outer shell and top cover. Utilizing the lightweight yet high-strength properties of carbon, the drone casing achieves both lightness and high strength, preventing deformation under impacts and other external forces. It also provides good heat resistance, preventing heat buildup inside the casing from affecting its performance. An aluminum reinforcing frame is sandwiched between the carbon-based outer shell and top cover. Aluminum's lightweight and good ductility ensure the drone casing remains lightweight while providing stable support between the two components under impacts. Through deformation, it effectively absorbs and disperses impact energy, preventing stress concentration at the joint and potential breakage. Furthermore, aluminum's superior thermal conductivity compared to carbon allows the aluminum reinforcing frame to rapidly dissipate heat from both the carbon-based outer shell and top cover into the air. By utilizing a carbon-aluminum sandwich structure, the drone shell possesses excellent bending resistance, compressive strength, and heat dissipation performance, thereby maintaining structural stability while the drone shell bears a large load. Attached Figure Description

[0020] The technical solution of this utility model will be further described in detail below with reference to the accompanying drawings and embodiments. In the accompanying drawings:

[0021] Figure 1 This is a schematic diagram of the overall structure of the drone casing provided in an embodiment of the present utility model;

[0022] Figure 2 This is an exploded view of the structure of the drone casing provided in an embodiment of the present invention;

[0023] Figure 3 A cross-sectional structural diagram of the drone casing provided in an embodiment of this utility model;

[0024] Figure 4A schematic diagram of the overall structure of the UAV provided in this embodiment of the utility model;

[0025] Figure 5 An exploded view of the structure of the UAV provided in this embodiment of the utility model.

[0026] The markings in the attached diagram are as follows:

[0027] 1. Carbon-based outer shell; 11. Battery compartment; 12. Control compartment; 121. Second mounting hole; 2. Carbon-based top cover; 21. Cover plate; 22. Support boss; 3. Aluminum reinforcing frame; 4. Extension frame; 41. First horizontal plate; 42. Second horizontal plate; 43. Vertical plate; 44. Assembly hole; 5. Carbon-based partition plate; 51. First mounting hole; 6. Carbon-based wing rod; 61. Carbon-based mounting base; 7. Battery assembly; 8. Electronic control assembly; 81. Flight control board; 82. Power distribution and ESC board; 9. Flight assembly; 91. Drive motor; 92. Propeller. Detailed Implementation

[0028] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The preferred embodiments of this utility model will now be described in detail with reference to the accompanying drawings.

[0029] This utility model discloses a drone casing, such as Figures 1-3 As shown, the device includes a carbon-based outer shell 1, a carbon-based top cover 2, and an aluminum reinforcing frame 3. A battery compartment 11 is housed within the carbon-based outer shell 1, and the battery compartment 11 has an opening on the carbon-based outer shell 1. The carbon-based top cover 2 is positioned corresponding to the opening and is aligned with the carbon-based outer shell 1, and is configured to contact the battery housed within the battery compartment 11. The aluminum reinforcing frame 3 is positioned between the carbon-based outer shell 1 and the carbon-based top cover 2, and the connection between the carbon-based top cover 2 and the carbon-based outer shell 1 forms a one-piece casing with a carbon-aluminum sandwich structure.

[0030] In the implementation of the above-described drone casing embodiment, the carbon-based outer shell 1 and the carbon-based top cover 2 are preferably made of carbon fiber or graphite, and constitute the main body of the drone casing. Utilizing the lightweight and high-strength properties of carbon materials, the drone casing can be ensured to be both lightweight and strong, making it less prone to deformation when subjected to impacts or other external forces. Simultaneously, the good thermal conductivity of carbon fiber or graphite materials contributes to the drone casing's excellent heat resistance, thus preventing heat buildup inside the casing from affecting its performance. Furthermore, an aluminum reinforcing frame 3 is sandwiched between the carbon-based outer shell 1 and the carbon-based top cover 2. Utilizing the good ductility of aluminum, the aluminum reinforcing frame 3 can stably support the drone between the carbon-based outer shell 1 and the carbon-based top cover 2 when subjected to impacts or other external forces. Through slight deformation, it effectively absorbs and disperses impact energy, preventing stress from directly concentrating at the joint between the carbon-based outer shell 1 and the carbon-based top cover 2, thus preventing breakage. Meanwhile, due to the lightweight and relatively high strength (though lower than carbon), the aluminum reinforcement frame 3 allows the drone casing to maintain its lightweight properties while further enhancing the strength of the carbon-based outer shell 1 and the carbon-based top cover 2. Furthermore, aluminum's superior thermal conductivity compared to carbon allows the aluminum reinforcement frame 3 to rapidly dissipate heat from both the carbon-based outer shell 1 and the carbon-based top cover 2 into the air. This integrated carbon-aluminum structure provides the drone casing with excellent bending, compressive, heat resistance, heat dissipation, and corrosion resistance, maintaining structural stability even under heavy loads. The carbon-based top cover 2 is configured to contact the battery housed in the battery compartment 11, allowing it to directly contact the battery surface for rapid heat conduction, which is then quickly dissipated into the air via the aluminum reinforcement frame 3.

[0031] Furthermore, the aluminum reinforcing frame 3 is placed flat on the opening of the carbon-based outer shell 1, and the aluminum reinforcing frame 3 has a ring structure corresponding to the opening. The carbon-based top cover 2 includes a cover plate 21 and a support boss 22 disposed on the bottom surface of the cover plate 21 and mating with the opening. After the carbon-based top cover 2 and the carbon-based outer shell 1 are mated, the aluminum reinforcing frame 3 fits onto the side wall of the support boss 22 and provides support between the opening of the carbon-based outer shell 1 and the cover plate 21.

[0032] Through the implementation of the above-described drone casing embodiment, since an aluminum reinforcing frame 3 is sandwiched between the carbon-based outer shell 1 and the carbon-based top cover 2, the carbon-based top cover 2, composed of a cover plate 21 and a supporting boss 22, allows the supporting boss 22 to pass through the aluminum reinforcing frame 3 after it is aligned with the carbon-based outer shell 1. It then fits into the carbon-based outer shell 1 through the opening, allowing the bottom of the supporting boss 22 to contact the battery installed in the battery compartment 11 without being affected by the aluminum reinforcing frame 3, thus enabling rapid heat conduction to the battery. At this time, the cover plate 21 completely seals the opening of the carbon-based outer shell 1, and the aluminum reinforcing frame 3 fits snugly onto the supporting boss 22. Because the aluminum reinforcing frame 3 is ductile, it is easily deformed by impact. Under this structure, the supporting boss 22 supports the inner wall of the aluminum reinforcing frame 3, thereby preventing the aluminum reinforcing frame 3 from bending inward and deforming after being subjected to external impact. It only plays the role of stabilizing the support between the carbon-based outer shell 1 and the carbon-based top cover 2, and effectively absorbing and dispersing the impact energy, thereby improving the stability of the UAV shell.

[0033] Furthermore, the aluminum reinforcing frame 3 is provided with an extension frame 4 located outside the carbon-based outer shell 1, so that the extension frame 4 can be used for accessory installation.

[0034] Through the implementation of the above-described drone casing embodiment, since the aluminum reinforcing frame 3 is placed flat on the open end of the carbon-based outer shell 1, the extension frame 4 extending from the aluminum reinforcing frame 3 eliminates the need for additional clearance structures on the drone casing, allowing the extension frame 4 to be directly positioned on one side of the drone. This simplifies the drone casing structure by directly installing necessary accessories, such as sensors and cameras, onto the extension frame 4, modularly integrating multiple accessories. This avoids complex drone casing structures and numerous interfaces. Furthermore, the integrated structure formed by assembling the carbon-based outer shell 1, carbon-based top cover 2, and aluminum reinforcing frame 3 reduces the weight of the drone casing, effectively improving the drone's flight performance and endurance.

[0035] Furthermore, the extension frame 4 includes a first horizontal plate 41, a second horizontal plate 42, and a vertical plate 43. The first horizontal plate 41 is integrally formed with the outer ring wall of the aluminum reinforcing frame 3, and the vertical plate 43 connects the first horizontal plate 41 and the second horizontal plate 42, forming a "Z"-shaped structure for the extension frame 4. The second horizontal plate 42 has several mounting holes 44.

[0036] Through the implementation of the above-described UAV casing embodiment, the first horizontal plate 41 of the extension frame 4 is integrally formed with the outer ring wall of the aluminum reinforcing frame 3. After the carbon-based outer shell 1 and the carbon-based top cover 2 are connected and clamped to fix the aluminum reinforcing frame 3, the first horizontal plate 41 of the extension frame 4 rests horizontally on the outer edge of the open opening of the carbon-based outer shell 1, providing stable support for the first horizontal plate 41 of the extension frame 4. The second horizontal plate 42 is used for accessory installation, ensuring the stability of the accessories and reducing inconsistencies between the accessories and the UAV's attitude caused by UAV vibration or airflow during flight. Furthermore, the vertical plate 43 connects the first horizontal plate 41 and the second horizontal plate 42 to form a "Z"-shaped structure for the extension frame 4, ensuring good structural stability and evenly distributing the force, reducing deformation or damage caused by uneven force distribution. Preferably, the extension frame 4 is also made of aluminum, ensuring it is lightweight and has good strength.

[0037] Furthermore, a carbon-based partition plate 5 is provided inside the carbon-based outer shell 1, which divides the internal space of the carbon-based outer shell 1 into a battery compartment 11 located above and a control compartment 12 located below. The battery compartment 11 has space for stacking and laying batteries flat, and the compartment structure of the battery compartment 11 is configured to correspond to the battery structure. The control compartment 12 is used to arrange the control circuit board.

[0038] In the implementation of the above-described UAV shell embodiment, the carbon-based partition plate 5 is selected as carbon fiber or graphite material. The carbon-based partition plate 5 divides the internal space of the carbon-based shell 1 into a battery compartment 11 and a control compartment 12, making full use of the internal space of the carbon-based shell 1. This allows for flexible allocation of the internal space, facilitating the independent design and replacement of different functional modules. For example, the battery compartment 11 is used to assemble large-capacity batteries, while the control compartment 12 is used to house control circuit boards. The carbon-based partition plate 5 protects these sensitive components from the heat generated by the batteries in the battery compartment 11 or other potential heat sources, and further prevents circuit failures caused by contact between different functional modules due to internal pressure or external impact. Furthermore, the internal space of the battery compartment 11 provides space for stacking and laying batteries flat, allowing batteries to be arranged at maximum density, thereby storing more battery energy within a limited space. The compartment structure is configured to correspond to the battery structure, making the battery compartment 11 also suitable for assembling heterogeneous batteries.

[0039] Furthermore, the carbon-based partition plate 5 is fitted inside the carbon-based outer shell 1, and a set of opposing sidewalls of the carbon-based partition plate 5 form wire-passing gaps with the inner wall of the carbon-based outer shell 1. The carbon-based partition plate 5 is provided with a plurality of first fixing holes 51, and the bottom surface of the control compartment 12 is provided with a plurality of second fixing holes 121 corresponding one-to-one with the first fixing holes 51. Connecting bolts are provided between the first fixing holes 51 and the corresponding second fixing holes 121.

[0040] In the implementation of the above-described UAV casing embodiment, the carbon-based partition plate 5 is selected as carbon fiber or graphite material. The wiring gap between the sidewall of the carbon-based partition plate 5 and the inner wall of the carbon-based outer shell 1 facilitates the wiring between the control board in the control compartment 12 and the battery in the battery compartment 11. The first fixing hole 51 on the carbon-based partition plate 5 corresponds to the second fixing hole 121 on the bottom surface of the control compartment 12, allowing the carbon-based partition plate 5 to be connected to the carbon-based outer shell 1 using connecting bolts. By tightening the connecting bolts, the carbon-based partition plate 5 fixes the control board to be installed on the bottom surface of the control compartment 12, preventing the control board from moving or falling off due to UAV vibration or airflow during flight. Furthermore, after the UAV is assembled, the carbon-based partition plate 5 adheres to the lower surface of the battery. The good thermal conductivity of carbon fiber or graphite ensures rapid heat dissipation from the battery, further protecting sensitive components on the control board from the heat generated by the battery in the battery compartment 11.

[0041] Furthermore, the battery compartment 11 has several heat dissipation holes penetrating the carbon-based outer shell 1 on its wall, and the battery compartment 11 has a first heat dissipation fin for separating the battery compartment 11 and the battery, and / or a second heat dissipation fin for separating the battery and adjacent batteries.

[0042] Through the implementation of the above-described drone casing embodiment, the heat dissipation holes in the battery compartment 11 allow air to circulate within it. Convection is generated through temperature differences, enabling rapid dissipation of heat from inside the battery compartment 11 to the external environment, thereby reducing the temperature inside the battery compartment 11 and preventing heat accumulation within the carbon-based outer shell 1. Simultaneously, the first heat sink separates the battery compartment 11 and the battery, reducing direct heat transfer from the battery to the carbon-based outer shell 1 and protecting its performance from high temperatures. The second heat sink separates adjacent batteries, helping to disperse heat generated between them and further preventing heat accumulation within the carbon-based outer shell 1. It also effectively prevents direct contact between batteries, reducing the risk of short circuits or overheating.

[0043] Furthermore, the carbon-based outer shell 1 is provided with carbon-based wing rods 6 distributed in four directions. One end of the carbon-based wing rod 6 is integrally formed with the outer wall of the carbon-based outer shell 1, and the other end of the carbon-based wing rod 6 is provided with a carbon-based mounting base 61 so that the carbon-based mounting base 61 can be used for mounting the flight propeller.

[0044] In the implementation of the above-described drone casing embodiment, the carbon-based wing rod 6 is selected as carbon fiber or graphite material. Integrating the carbon-based wing rod 6 with the carbon-based outer shell 1 as a single unit significantly reduces the manufacturing cost of the drone casing. This means that drone casings can be mass-produced directly using existing drone casing manufacturing equipment, eliminating the need to manufacture individual parts of the drone casing separately and then assemble them. Simultaneously, utilizing the lightweight and high-strength properties of carbon materials ensures that the carbon-based wing rod 6 maintains high strength while remaining lightweight, making it less prone to deformation when subjected to impacts or other external forces.

[0045] This utility model also discloses a drone, such as Figure 4 and Figure 5 As shown, the system includes the aforementioned drone casing, a battery assembly 7 housed within the battery compartment 11, an electronic control assembly 8 housed within the drone casing, and a flight assembly 9 mounted on the drone casing. The battery assembly 7 comprises multiple battery cells laid flat within the battery compartment 11. Each battery cell comprises multiple individual battery cells stacked and connected in series to form a battery pack, and the battery compartment 11 has a main power port for connecting the multiple laid-flat battery cells in parallel. The electronic control assembly 8 comprises a flight control board 81 and a power distribution board 82 laid flat. The power distribution board 82 is electrically connected to both the main power port and the flight control board 81, and is also electrically connected to the flight assembly 9.

[0046] Through the implementation of the above-described drone casing embodiment, utilizing the carbon-based outer shell 1, carbon-based top cover 2, and aluminum reinforcing frame 3 included in the drone casing, the entire drone possesses excellent bending resistance, pressure resistance, heat resistance, heat dissipation, and corrosion resistance. This allows the drone to maintain structural stability while bearing significant loads and rapidly dissipates heat accumulated inside the drone casing into the air, effectively improving the drone's durability and impact resistance. Furthermore, the battery cells are preferably lithium batteries. Two preferred battery cells are stacked and connected in series to form a battery pack, and two preferred groups of battery cells are connected in parallel to form a larger battery pack to power the drone. This increases the total capacity of the battery assembly 7 while maintaining a low voltage, effectively improving the drone's flight performance and endurance. Multiple large-capacity battery cells can be laid flat within the limited battery compartment 11, maximizing the use of the longitudinal and lateral space within the compartment. Compared to the traditional drone solution of simply stacking multiple batteries, this embodiment uses a flat arrangement of multiple battery cells, increasing the surface area of ​​the battery cells exposed to air and thus providing better heat dissipation.

[0047] As described above, the flight control board 81 mainly receives signals from the remote controller via a receiver and connects to the power distribution ESC board 82 via a series of signal lines, such as PPM or PWM signals. The power distribution ESC board 82 then controls the rotation speed and direction of the flight component 9 based on these signals. The power distribution ESC board 82 is connected to the main power port of the battery pack 7 to distribute power to the flight control board 81 and the flight component 9, ensuring that the flight component 9 receives sufficient power during the drone's flight.

[0048] Furthermore, the flight assembly 9 includes a drive motor 91 and a propeller 92 connected to the output of the drive motor 91. The flight assemblies 9 are distributed in four directions on the UAV fuselage, and the four drive motors 91 are electrically connected to the power distribution board 82.

[0049] Through the implementation of the above-described UAV casing embodiment, the drive motor 91 drives the propeller 92 to rotate, providing power for the UAV's flight. The flight components 9 distributed in four directions of the UAV casing provide the UAV with more stable flight and controllability, enabling the UAV to perform more precise quadcopter flight, including ascent, descent, forward, backward, left turn, right turn, and hovering. Simultaneously, the four drive motors 91 are electrically connected to the power distribution and electronic speed control board 82, allowing each drive motor 91 to be controlled independently, thus achieving more flexible flight attitude adjustments. If one drive motor 91 or propeller 92 fails, the UAV can still maintain flight using the other three sets of flight components 9, improving the reliability and safety of UAV flight.

[0050] It should be understood that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Those skilled in the art can modify the technical solutions described in the above embodiments, or make equivalent substitutions for some of the technical features; and all such modifications and substitutions should fall within the protection scope of the appended claims of this utility model.

Claims

1. A drone casing, characterized in that: The drone casing includes a carbon-based outer shell, a carbon-based top cover, and an aluminum reinforcing frame. A battery compartment is disposed inside the carbon-based outer shell, and the battery compartment has an opening on the carbon-based outer shell. The carbon-based top cover is aligned with the carbon-based outer shell at the position corresponding to the opening, and the carbon-based top cover is configured to contact the battery installed in the battery compartment. The aluminum reinforcing frame is disposed between the carbon-based outer shell and the carbon-based top cover, and the carbon-based top cover and the carbon-based outer shell, when aligned, form an integrated casing with a carbon-aluminum structure.

2. The UAV casing according to claim 1, characterized in that: The aluminum reinforcing frame is placed flat on the opening of the carbon-based shell, and the aluminum reinforcing frame has a ring structure corresponding to the opening. The carbon-based top cover includes a cover plate and a support boss disposed on the bottom surface of the cover plate and mating with the opening. After the carbon-based top cover and the carbon-based shell are mated, the aluminum reinforcing frame fits onto the side wall of the support boss and is positioned between the opening of the carbon-based shell and the cover plate for support.

3. The UAV casing according to claim 2, characterized in that: The aluminum reinforcing frame is provided with an extension frame located outside the carbon-based outer shell, so that the extension frame can be used for accessory installation.

4. The UAV casing according to claim 3, characterized in that: The extension frame includes a first horizontal plate, a second horizontal plate, and a vertical plate. The first horizontal plate is integrally formed with the outer ring wall of the aluminum reinforcing frame. The vertical plate connects the first horizontal plate and the second horizontal plate, and the extension frame forms a "Z" shaped structure. The second horizontal plate has several assembly holes.

5. The UAV casing according to claim 1, characterized in that: The carbon-based shell is provided with a carbon-based partition plate, which divides the internal space of the carbon-based shell into the battery compartment located above and the control compartment located below. The battery compartment has space for stacking and laying batteries flat, and the compartment structure is configured to correspond to the battery structure. The control compartment is used to arrange the control board.

6. The UAV casing according to claim 5, characterized in that: The carbon-based partition plate is fitted inside the carbon-based outer shell, and a set of opposite sidewalls of the carbon-based partition plate form a wire-passing gap with the inner wall of the carbon-based outer shell. The carbon-based partition plate is provided with a plurality of first fixing holes, and the bottom surface of the control compartment is provided with a plurality of second fixing holes corresponding one-to-one with the first fixing holes. Connecting bolts are provided between the first fixing holes and the corresponding second fixing holes.

7. The UAV casing according to claim 5, characterized in that: The battery compartment wall is provided with several heat dissipation holes penetrating the carbon-based outer shell, and the battery compartment is provided with a first heat dissipation fin for separating the battery compartment and the battery, and / or a second heat dissipation fin for separating the battery and adjacent batteries.

8. The UAV casing according to claim 1, characterized in that: The carbon-based outer shell is provided with carbon-based wing rods distributed in four directions. One end of the carbon-based wing rod is integrally formed with the outer wall of the carbon-based outer shell, and the other end of the carbon-based wing rod is provided with a carbon-based mounting base so that the carbon-based mounting base can be used for mounting the flight propeller.

9. An unmanned aerial vehicle (UAV), characterized in that: The drone includes a drone housing as described in any one of claims 1-8, a battery assembly disposed in the battery compartment, an electronic control assembly disposed in the drone housing, and a flight assembly disposed on the drone housing; The battery assembly includes multiple battery cells laid flat in the battery compartment. Each battery cell includes multiple individual battery cells stacked and connected in series to form a battery pack. The battery compartment is provided with a main power port that connects the multiple laid-flat battery cells in parallel. The electronic control assembly includes a flight control board and a power distribution board laid flat. The power distribution board is electrically connected to the main power port and the flight control board, respectively, and is also electrically connected to the flight assembly.

10. The UAV according to claim 9, characterized in that: The flight components include drive motors and propellers connected to the output of the drive motors. The flight components are distributed in four directions on the UAV casing, and the four drive motors are electrically connected to the power distribution board.

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