A fuel cell drone

Abstract

This utility model relates to the field of unmanned aerial vehicle (UAV) technology and discloses a fuel cell UAV, including a fuselage, a flight control system, a connecting frame, a hydrogen storage tank, and a fuel cell module. The fuselage includes a wing assembly, a frame, and a bay, with the wing assembly and bay respectively connected to the frame. The flight control system is located on top of the bay and is electrically connected to the wing assembly for controlling its operation. The connecting frame is located inside the bay. The hydrogen storage tank is connected to the connecting frame for storing hydrogen. The fuel cell module is located inside the bay and connected to the connecting frame, positioned above or below the hydrogen storage tank, and connected to receive hydrogen from the tank. The fuel cell module is electrically connected to the flight control system and the wing assembly to supply power to them. This utility model independently configures the flight control system, fuel cell module, and hydrogen storage tank, facilitating individual maintenance of each component.

Description

Technical Field

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

[0002] Fuel cell drones use hydrogen fuel cells as their core power source. The hydrogen they carry reacts with naturally inhaled oxygen in the presence of a catalyst to generate electricity, propelling the drone's flight. They offer advantages such as ultra-long endurance and low-temperature tolerance, and can conveniently and efficiently collect data on power transmission line corridors, finding applications in power line inspection, high-altitude surveying, and emergency communications. Currently, fuel cell drones use small, air-cooled fuel cell stacks, integrating hydrogen tanks, DC-DC power converters, and flight control systems to achieve long-distance, heavy-load, multi-functional transportation. However, integrating the hydrogen tanks and flight control system onto the fuel cell stack makes refilling or replacing the hydrogen tanks difficult and hinders separate maintenance of the fuel cell and flight control system. Utility Model Content

[0003] The purpose of this invention is to provide a fuel cell drone to solve the problems of difficulty in filling or replacing hydrogen cylinders and inconvenience in separately maintaining fuel cells and flight control systems in the prior art.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] This utility model provides a fuel cell drone, comprising:

[0006] The fuselage includes a wing assembly, a frame, and a cabin, wherein the wing assembly and the cabin are respectively connected to the frame;

[0007] A flight control system is located on the top of the cabin. The flight control system is electrically connected to the wing assembly and is used to control the operation of the wing assembly.

[0008] The connecting frame is located inside the machine compartment;

[0009] A hydrogen storage cylinder, connected to a connecting frame, is used to store hydrogen gas; and

[0010] A fuel cell module is located inside the cabin and connected to the connecting frame. The fuel cell module is positioned above or below the hydrogen storage tank and is connected to the hydrogen storage tank to receive hydrogen gas from the tank. The fuel cell module is electrically connected to the flight control system and the wing assembly to supply power to the flight control system and the wing assembly.

[0011] In some embodiments, the fuel cell module includes:

[0012] A fuel cell stack has a top surface, a bottom surface, two first sides arranged opposite to each other, and two second sides arranged opposite to each other.

[0013] A controller is connected to one of the first sides;

[0014] The filter assembly is connected to the top surface;

[0015] A wiring harness frame, connected to the bottom surface, is used to arrange the wiring harness of the fuel cell stack;

[0016] A hydrogen pipeline is provided on the wiring harness frame, and the hydrogen pipeline connects the fuel cell stack and the hydrogen storage cylinder;

[0017] A heat sink is disposed below the wire harness frame and is connected to the wire harness frame.

[0018] In some embodiments, the filtration assembly includes a filter screen and a filter element, the filter element being disposed on the top surface of the fuel cell stack, the filter screen being disposed on the side of the filter element facing away from the fuel cell stack, and the filter screen being detachably connected to the fuel cell stack.

[0019] In some embodiments, the fuel cell module further includes insulating side covers, which are respectively connected to the two second side surfaces.

[0020] In some embodiments, the fuel cell module further includes a DC power converter disposed on the side of the insulating side cover away from the fuel cell stack, and the DC power converter is connected to the fuel cell stack and the flight control system.

[0021] In some embodiments, the housing includes a shell and a cover. The shell has a receiving cavity with an opening on one side. The cover is disposed on the opening and is detachably connected to the shell. The cover is detachably connected to the frame. The connecting frame, the hydrogen storage tank, and the fuel cell module are all located within the receiving cavity.

[0022] In some embodiments, the side wall of the compartment cover is provided with ventilation holes.

[0023] In some embodiments, the connecting frame includes a frame body, a first connector and a second connector. The frame body is connected to the engine compartment. The first connector and the second connector are respectively connected to the frame body. The first connector and the second connector are spaced apart vertically. The first connector divides the engine compartment into a first accommodating space and a second accommodating space. The fuel cell module is placed in the first accommodating space and the hydrogen storage cylinder is placed in the second accommodating space.

[0024] In some embodiments, fasteners are provided on both the side of the first connector facing the second connector and the side of the second connector facing the first connector, and the hydrogen storage cylinder is fixed to the fasteners.

[0025] In some embodiments, the frame includes an annular frame and a support, the annular frame being connected to the support, the annular frame having an inner edge and an outer edge, the wing assembly being connected to the outer edge of the annular frame, and the nacelle being connected to the inner edge of the annular frame.

[0026] Compared with the prior art, the beneficial effects of this utility model embodiment of a fuel cell drone are as follows:

[0027] This embodiment of the fuel cell drone features a frame and a bay on its fuselage, with the bay connected to the frame. The wing assembly is connected to the frame, and the flight control system is located on top of the bay. The hydrogen storage tank and fuel cell module are both housed within the bay, thus separating the flight control system from the hydrogen storage tank and fuel cell module, facilitating individual maintenance of the flight control system. A connecting frame is installed within the bay to connect both the hydrogen storage tank and fuel cell module. The fuel cell module is positioned above or below the hydrogen storage tank. This connection frame separates the fuel cell module from the hydrogen storage tank, facilitating refilling or replacement of the hydrogen storage tank and individual maintenance of the fuel cell module.

[0028] Therefore, this application, through the reasonable arrangement of the cabin and connecting frame, independently sets up the flight control system, fuel cell module and hydrogen storage tank, which facilitates the individual maintenance of the flight control system, fuel cell module and hydrogen storage tank. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the structure of the fuel cell drone described in this embodiment of the utility model;

[0030] Figure 2 This is an exploded view of the fuel cell drone described in this embodiment of the present invention;

[0031] Figure 3 This is a schematic diagram of the structure of the fuel cell module in an embodiment of this utility model;

[0032] Figure 4 This is a front view schematic diagram of the fuel cell module in an embodiment of this utility model;

[0033] Figure 5 This is a top view of the fuel cell module in an embodiment of this utility model;

[0034] Figure 6 This is a side view of the fuel cell module in an embodiment of the present invention;

[0035] Figure 7This is an exploded view of the fuel cell module in an embodiment of this utility model.

[0036] Numbering on the map:

[0037] 10. Airframe; 11. Wing assembly; 111. Connecting rod; 12. Frame; 121. Annular frame; 122. Support; 13. Navigation; 131. Shell; 1311. Receiving cavity; 132. Navigation cover; 1321. Vent; 20. Flight control system; 30. Connecting frame; 31. Frame body; 32. First connector; 33. Second connector; 34. Fastener; 40. Hydrogen storage tank; 50. Fuel cell module; 51. Fuel cell... 511. Top surface of the fuel cell stack; 512. First side surface; 513. Second side surface; 514. Hydrogen inlet; 515. Hydrogen outlet; 52. Controller; 53. Filter assembly; 531. Filter screen; 532. Filter element; 54. Wiring harness frame; 541. Wiring harness; 55. Hydrogen pipeline; 551. Solenoid valve; 56. Heat sink; 57. Insulating side cover; 58. DC power converter; 59. Individual cell voltage monitor. Detailed Implementation

[0038] In the description of this utility model, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this utility model. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0039] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0040] The specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples. The following examples are used to illustrate this utility model, but are not intended to limit its scope.

[0041] See Figure 1 and Figure 2As shown, this utility model embodiment provides a fuel cell unmanned aerial vehicle (UAV), including a body 10, a flight control system 20, a connecting frame 30, a hydrogen storage tank 40, and a fuel cell module 50. The body 10 includes a wing assembly 11, a frame 12, and a cabin 13. The wing assembly 11 and the cabin 13 are respectively connected to the frame 12. The flight control system 20 is located on the top of the cabin 13 and is electrically connected to the wing assembly 11. The flight control system 20 is used to control the operation of the wing assembly 11. The connecting frame 30 is provided with... The hydrogen storage tank 40 is located inside the cabin 13 and connected to the connecting frame 30. The hydrogen storage tank 40 is used to store hydrogen. The fuel cell module 50 is located inside the cabin 13 and connected to the connecting frame 30. The fuel cell module 50 is located above or below the hydrogen storage tank 40 and is connected to the hydrogen storage tank 40 to receive hydrogen from the hydrogen storage tank 40. The fuel cell module 50 is electrically connected to the flight control system 20 and the wing assembly 11 to supply power to the flight control system 20 and the wing assembly 11.

[0042] A frame 12 and a cabin 13 are mounted on the fuselage 10, connecting the cabin 13 to the frame 12. The wing assembly 11 is connected to the frame 12. The flight control system 20 is located on top of the cabin 13. The hydrogen storage tank 40 and the fuel cell module 50 are both housed within the cabin 13, thus separating the flight control system 20 from the hydrogen storage tank 40 and fuel cell module 50, facilitating individual maintenance of the flight control system 20. A connecting frame 30 is installed within the cabin 13, connecting both the hydrogen storage tank 40 and the fuel cell module 50. The fuel cell module 50 is positioned above or below the hydrogen storage tank 40. The connecting frame 30 separates the fuel cell module 50 from the hydrogen storage tank 40, facilitating refilling or replacement of the hydrogen storage tank 40 and individual maintenance of the fuel cell module 50. By rationally configuring the cabin 13 and the connecting frame 30, the flight control system 20, the fuel cell module 50, and the hydrogen storage tank 40 are set up independently, which facilitates the individual maintenance of the flight control system 20, the fuel cell module 50, and the hydrogen storage tank 40.

[0043] See Figure 1 and Figure 2As shown, in some embodiments, the frame 12 includes an annular frame 121 and a support 122. The annular frame 121 is connected to the support 122. The annular frame 121 has an inner edge and an outer edge. The wing assembly 11 is connected to the outer edge of the annular frame 121, and the cabin 13 is connected to the inner edge of the annular frame 121. The support 122 is used to support the entire fuel cell UAV, facilitating the placement of the entire fuel cell UAV on the ground or in other locations. The bottom of the support 122 protrudes downward from the cabin 13 to prevent the cabin 13 from contacting the ground. The annular frame 121 is rectangular, and the wing assembly 11 is connected to the four corners of the annular frame 121. The cabin 13 is detachably connected to the annular frame 121, for example, by bolts, which facilitates the disassembly and installation of the cabin 13, thereby facilitating the filling or replacement of the hydrogen storage tank 40 inside the cabin 13, or the maintenance of the fuel cell module 50.

[0044] It should be noted that the structural composition of the wing assembly 11 in this invention is prior art and will not be described in detail here. For example, the wing assembly 11 includes a motor and a wing, with the motor driving the wing to rotate. The wing assembly 11 can be connected to the annular frame 121 of the frame 12 via a connecting rod 111. The connection method between the flight control system 20 and the wing assembly 11 is prior art and will not be described in detail here.

[0045] See Figure 1 and Figure 2 As shown, in some embodiments, the cabin 13 includes a housing 131 and a cover 132. The housing 131 has a receiving cavity 1311 with an opening on one side. The cover 132 covers the opening and is detachably connected to the housing 131. The cover 132 is detachably connected to the frame 12. The connecting frame 30, the hydrogen storage tank 40, and the fuel cell module 50 are all located within the receiving cavity 1311. Designing the cabin 13 as a separate structure of the housing 131 and the cover 132 facilitates the connection between the cabin 13 and the frame 12. Furthermore, by separating the housing 131 and the cover 132, the housing 131 can be removed from the cover 132, making it easier to remove the hydrogen storage tank 40 and the fuel cell module 50 from inside the housing 131. This allows for maintenance of the hydrogen storage tank 40 and the fuel cell module 50 without disassembling the cover 132 and the flight control system 20. The side wall of the cover 132 is provided with a vent hole 1321, which connects the receiving cavity 1311 inside the housing 131 with the outside, so as to realize the airflow between the receiving cavity 1311 and the outside.

[0046] See Figure 2As shown, in some embodiments, the connecting frame 30 includes a frame body 31, a first connecting member 32, and a second connecting member 33. The frame body 31 is connected to the cabin 13. The first connecting member 32 and the second connecting member 33 are respectively connected to the frame body 31. The first connecting member 32 and the second connecting member 33 are spaced vertically apart. The first connecting member 32 divides the cabin 13 into a first accommodating space and a second accommodating space. The fuel cell module 50 is placed in the first accommodating space, and the hydrogen storage tank 40 is placed in the second accommodating space. The frame body 31 is detachably connected to the shell 131 of the cabin 13. The first connecting member 32 provides not only an installation carrier and support for the hydrogen storage tank 40, but also support for the fuel cell module 50. The second connecting member 33 provides an installation carrier and support for the hydrogen storage tank 40. The first connecting member 32 and the second connecting member 33 are provided with multiple through holes, which not only facilitates heat dissipation of the fuel cell module 50 and facilitates the connection of hydrogen pipelines between the hydrogen storage tank 40 and the fuel cell module 50, but also helps to reduce the overall weight of the UAV.

[0047] See Figure 2 As shown, in some embodiments, fasteners 34 are provided on both the side of the first connector 32 facing the second connector 33 and the side of the second connector 33 facing the first connector 32, and the hydrogen storage cylinder 40 is fixed to the fasteners 34. Two rows of hydrogen storage cylinders 40 can be arranged, with one row fixed to the first connector 32 and the other row fixed to the second connector 33. The fasteners 34 are snap fasteners. Fixing the hydrogen storage cylinders 40 with the fasteners 34 facilitates the disassembly of the hydrogen storage cylinders 40. Each hydrogen storage cylinder 40 is provided with at least two fasteners 34, and these at least two fasteners 34 are spaced apart along the length of the hydrogen storage cylinder 40 to ensure the stability of the fixation of the hydrogen storage cylinder 40.

[0048] See Figures 3-7As shown, in some embodiments, the fuel cell module 50 includes a fuel cell stack 51, a controller 52, a filter assembly 53, a wiring harness 54, a hydrogen pipeline 55, and a heat sink 56. The fuel cell stack 51 has a top surface 511, a bottom surface, two opposing first side surfaces 512, and two opposing second side surfaces 513. The controller 52 is connected to one of the first side surfaces 512, and the other first side surface 512 of the fuel cell stack 51 has a hydrogen inlet 514 and a hydrogen outlet 515. The filter assembly 53 is connected to the top surface 511 and is used to filter the air entering the fuel cell stack 51. The filter assembly 53 can be connected to the casing. Ventilation holes 1321 on the side wall of cover 132 are opposite each other; wire harness frame 54 is connected to the bottom surface and is used to arrange the wire harness 541 of fuel cell stack 51, including metal wires for transmitting electrical energy and cables for transmitting signals; hydrogen pipeline 55 is provided on wire harness frame 54, and hydrogen pipeline 55 connects fuel cell stack 51 and hydrogen storage tank 40, specifically connected to hydrogen inlet 514, so as to transport hydrogen in hydrogen storage tank 40 to fuel cell stack 51, and a solenoid valve 551 is provided on hydrogen pipeline 55; heat sink 56 is provided below wire harness frame 54 and is connected to wire harness frame 54, and dissipates the heat generated by fuel cell stack 51 during operation through heat sink 56. Heat sink 56 is a cooling fan, and heat sink 56 is electrically connected to controller 52, and the operation of heat sink 56 is controlled by controller 52. The controller 52 is the control unit of the fuel cell module 50. The controller 52 is also electrically connected to the solenoid valve 551 on the hydrogen pipeline 55 to control the operation of the solenoid valve 551. Integrating the controller 52, filter assembly 53, wiring harness 54, hydrogen pipeline 55, and heat sink 56 around the fuel cell stack 51 improves the integration level of the fuel cell module 50, reduces its space occupation in the compartment 13, and thus reduces the overall volume of the compartment 13.

[0049] It should be noted that in this invention, the fuel cell stack 51 is used to chemically react hydrogen as fuel with inhaled oxygen under the action of a catalyst to generate electrical energy, thereby powering the drone. The structural composition of the fuel cell stack 51 is prior art and will not be described in detail in this invention.

[0050] See Figure 7 As shown, in some embodiments, the filter assembly 53 includes a filter screen 531 and a filter element 532. The filter element 532 is disposed on the top surface 511 of the fuel cell stack 51, and the filter screen 531 is disposed on the side of the filter element 532 facing away from the fuel cell stack 51. The filter screen 531 is detachably connected to the fuel cell stack 51. Air enters through the filter screen 531, is filtered by the filter element 532, and then enters the fuel cell stack 51 to react chemically with hydrogen. Dust and other impurities in the air can be filtered out by the filter screen 531 and the filter element 532.

[0051] See Figures 3-7 As shown, in some embodiments, the fuel cell module 50 further includes insulating side covers 57, respectively connected to two second side covers 513. The insulating side covers 57 isolate the fuel cell stack 51 from external devices. The fuel cell module 50 also includes a DC power converter 58, disposed on the side of the insulating side covers 57 opposite to the fuel cell stack 51. The DC power converter 58 is connected to the fuel cell stack 51 and the flight control system 20. The DC power converter 58 establishes a connection between the fuel cell stack 51 and the flight control system 20, supplying DC power to the flight control system 20. The DC power converter 58 is electrically connected to a controller 52 within the fuel cell module 50.

[0052] See Figure 7 As shown, in some embodiments, the fuel cell module 50 further includes a cell voltage monitor 59 (CVM) for monitoring the voltage of each cell in the fuel cell stack 51. The cell voltage monitor 59 is electrically connected to the controller 52 to transmit the collected voltage signal to the controller 52. The cell voltage monitor 59 and the controller 52 are arranged side by side on the first side 512.

[0053] The working process of this utility model is as follows:

[0054] The flight control system 20 controls the operation of the wing assembly 11, supplies hydrogen to the fuel cell stack 51 via the hydrogen storage tank 40, and supplies power to the flight control system 20 via the fuel cell stack 51. The flight control system 20 then controls the operation of the wing assembly 11. When it is necessary to refill, replace, or maintain the hydrogen storage tank 40 or the fuel cell module 50, simply disassemble the housing 131 and the cover 132 to remove the hydrogen storage tank 40 and fuel cell module 50 from the housing 131 without affecting the connection between the cover 132 and the frame 12. When maintenance of the flight control system 20 is required, simply remove the flight control system 20 from the cover 132 without affecting the hydrogen storage tank 40 and fuel cell module 50 inside the cabin 13.

[0055] In summary, this utility model embodiment provides a fuel cell drone that separates the flight control system 20 from the hydrogen storage tank 40 and the fuel cell module 50, facilitating individual maintenance of the flight control system 20. A connecting frame 30 is provided within the cabin 13, connecting both the hydrogen storage tank 40 and the fuel cell module 50. The fuel cell module 50 is positioned above or below the hydrogen storage tank 40. The connecting frame 30 separates the fuel cell module 50 from the hydrogen storage tank 40, facilitating refilling or replacement of the hydrogen storage tank 40 and individual maintenance of the fuel cell module 50. Through the rational arrangement of the cabin 13 and the connecting frame 30, the flight control system 20, the fuel cell module 50, and the hydrogen storage tank 40 are independently configured, facilitating individual maintenance of each component.

[0056] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present utility model, and these improvements and substitutions should also be considered within the protection scope of the present utility model.

Claims

1. A fuel cell drone, characterized by, include: Airframe (10), the airframe (10) includes wing assembly (11), frame (12) and cabin (13), the wing assembly (11) and the cabin (13) are respectively connected to the frame (12); A flight control system (20) is located on the top of the cabin (13). The flight control system (20) is electrically connected to the wing assembly (11). The flight control system (20) is used to control the operation of the wing assembly (11). A connecting frame (30) is provided inside the machine compartment (13); A hydrogen storage cylinder (40), connected to a connecting frame (30), the hydrogen storage cylinder (40) being used to store hydrogen gas; and A fuel cell module (50) is located inside the cabin (13). The fuel cell module (50) is connected to the connecting frame (30). The fuel cell module (50) is located above or below the hydrogen storage tank (40). The fuel cell module (50) is connected to the hydrogen storage tank (40) to receive hydrogen gas from the hydrogen storage tank (40). The fuel cell module (50) is electrically connected to the flight control system (20) and the wing assembly (11) to supply power to the flight control system (20) and the wing assembly (11).

2. The fuel cell drone of claim 1, wherein, The fuel cell module (50) includes: The fuel cell stack (51) has a top surface (511), a bottom surface, two first side surfaces (512) arranged opposite to each other, and two second side surfaces (513) arranged opposite to each other; A controller (52) is connected to one of the first sides (512); A filter assembly (53) is attached to the top surface (511); A wiring harness frame (54), connected to the bottom surface, is used to arrange the wiring harness (541) of the fuel cell stack (51); A hydrogen pipeline (55) is provided on the wire harness frame (54), and the hydrogen pipeline (55) connects the fuel cell stack (51) and the hydrogen storage cylinder (40); A heat sink (56) is disposed below the wire harness frame (54), and the heat sink (56) is connected to the wire harness frame (54).

3. The fuel cell drone of claim 2, wherein, The filter assembly (53) includes a filter screen (531) and a filter element (532). The filter element (532) is disposed on the top surface (511) of the fuel cell stack (51). The filter screen (531) is disposed on the side of the filter element (532) facing away from the fuel cell stack (51). The filter screen (531) is detachably connected to the fuel cell stack (51).

4. The fuel cell drone according to claim 2, characterized in that, The fuel cell module (50) also includes an insulating side cover (57) which is connected to the two second side surfaces (513) respectively.

5. The fuel cell drone according to claim 4, characterized in that, The fuel cell module (50) also includes a DC power converter (58) disposed on the side of the insulating side cover (57) away from the fuel cell stack (51). The DC power converter (58) is connected to the fuel cell stack (51) and the flight control system (20).

6. The fuel cell drone according to claim 1, characterized in that, The housing (13) includes a shell (131) and a cover (132). The shell (131) has a receiving cavity (1311) with an opening on one side. The cover (132) covers the opening and is detachably connected to the shell (131). The cover (132) is detachably connected to the frame (12). The connecting frame (30), the hydrogen storage cylinder (40), and the fuel cell module (50) are all located in the receiving cavity (1311).

7. The fuel cell drone according to claim 6, characterized in that, The side wall of the cover (132) is provided with a vent (1321).

8. The fuel cell drone according to claim 1, characterized in that, The connecting frame (30) includes a frame (31), a first connector (32), and a second connector (33). The frame (31) is connected to the engine compartment (13). The first connector (32) and the second connector (33) are respectively connected to the frame (31). The first connector (32) and the second connector (33) are arranged vertically at intervals. The first connector (32) divides the engine compartment (13) into a first accommodating space and a second accommodating space. The fuel cell module (50) is placed in the first accommodating space, and the hydrogen storage cylinder (40) is placed in the second accommodating space.

9. The fuel cell drone according to claim 8, characterized in that, The first connector (32) is provided with fasteners (34) on the side facing the second connector (33) and the second connector (33) is provided with fasteners (34) on the side facing the first connector (32), and the hydrogen storage bottle (40) is fixed to the fasteners (34).

10. The fuel cell drone according to claim 1, characterized in that, The frame (12) includes an annular frame (121) and a support (122). The annular frame (121) is connected to the support (122). The annular frame (121) has an inner edge and an outer edge. The wing assembly (11) is connected to the outer edge of the annular frame (121), and the cabin (13) is connected to the inner edge of the annular frame (121).

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