A fixed-wing unmanned aerial vehicle based on a methanol fuel cell

Abstract

The utility model discloses a fixed wing unmanned plane based on methanol fuel cell belongs to unmanned plane technical field, the utility model discloses a unmanned plane body, and the methanol fuel cell power generation system, lithium battery group, electric power management and distribution system, methanol fuel storage and supply system and flight control system integrated in the unmanned plane body inside, the utility model effectively solved the pure battery unmanned plane short, pure hydrogen fuel cell unmanned plane fuel storage carries inconvenient etc. problem, both utilize the long endurance advantage of fuel cell, and through lithium battery, make unmanned plane both long time cruising, and can cope with complex flight task again.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a fixed-wing UAV based on a methanol fuel cell. Background Technology

[0002] Fixed-wing drones have been widely used in surveying, agriculture, power line inspection, border patrol, and communication relay due to their high cruising efficiency and relatively strong payload capacity. However, most fixed-wing drones currently use lithium batteries as their power source, which have limited energy density (usually below 300Wh / kg), resulting in generally short flight times, mostly between 1 and 4 hours, making it difficult to meet the needs of long-duration, large-scale operations.

[0003] Fuel cells, especially proton exchange membrane fuel cells, are considered an ideal power solution for long-endurance drones due to their high energy density. Among them, hydrogen fuel cell technology is relatively mature, but hydrogen storage and transportation present significant challenges. High-pressure gaseous hydrogen storage has low volumetric energy density, while liquid hydrogen storage requires extremely low temperature environments, resulting in high costs and stringent safety requirements, making it unsuitable for drone platforms that require frequent takeoffs and landings and operate in the field.

[0004] Methanol, as a liquid fuel, boasts advantages such as high energy density (approximately 4300 Wh / L, far exceeding that of lithium batteries), ease of transportation, rapid refueling, and safe storage. Direct methanol fuel cells or methanol reformed fuel cells produced through a reformer can effectively utilize the chemical energy in methanol to generate electricity. However, integrating methanol fuel cell systems into space-constrained, weight- and balance-sensitive fixed-wing drones (UAVs) and achieving stable, efficient, and long-term operation still faces numerous technical challenges. These include: slow dynamic response of the fuel cell system, making it difficult to meet the instantaneous high-power demands of the UAV; complex system heat dissipation management; compact integration with the UAV structure; and center-of-gravity control during flight.

[0005] Therefore, there is an urgent need for a fixed-wing unmanned aerial vehicle (UAV) system solution that can fully leverage the high energy density of methanol fuel cells while overcoming their drawbacks such as slow dynamic response and integration difficulties, thereby achieving ultra-long endurance. Utility Model Content

[0006] The purpose of this invention is to provide a fixed-wing unmanned aerial vehicle based on a methanol fuel cell.

[0007] To achieve the above objectives, the technical solution adopted by this utility model is as follows: A fixed-wing unmanned aerial vehicle (UAV) based on a methanol fuel cell includes a UAV body, a methanol fuel cell power generation system integrated inside the UAV body as the main power source for the UAV, and a lithium battery pack as an auxiliary power source for the UAV, a power management and distribution system connected to the methanol fuel cell power generation system and the lithium battery pack, a methanol fuel storage and supply system connected to the methanol fuel cell power generation system for supplying fuel to the methanol fuel cell power generation system, and a flight control system connected to the power management and distribution system; the flight control system uses an HPM6750 flight control computer.

[0008] Furthermore, the methanol fuel cell power generation system can be a direct methanol fuel cell system or a reformed methanol fuel cell system.

[0009] Furthermore, the input end of the power management and distribution system is connected to the methanol fuel cell power generation system and the lithium battery pack, and the output end is connected to a DC bus.

[0010] Furthermore, the power management and distribution system includes a bidirectional DC / DC converter and a fuel cell controller; the bidirectional DC / DC converter is connected between the lithium battery pack and the DC bus; the fuel cell controller is connected to the bidirectional DC / DC converter, the methanol fuel cell power generation system, the lithium battery pack, and the flight control system via a communication bus.

[0011] Furthermore, the fuel cell controller employs an embedded microcontroller.

[0012] Furthermore, the methanol fuel storage and supply system includes one or more methanol fuel tanks, which are connected to the methanol fuel cell power generation system via supply pipelines; the methanol fuel tanks are symmetrically arranged at the center of gravity of the fuselage.

[0013] Furthermore, the methanol fuel storage and supply system also includes a quick refueling interface and a fuel quantity sensor; the quick refueling interface is located on the side of the fuselage and is connected to the methanol fuel tank via a refueling pipeline; the fuel quantity sensor is integrated inside the methanol fuel tank and connected to the flight control system.

[0014] Furthermore, the UAV body adopts a blended wing-body structure; the central fuselage of the blended wing-body structure houses an integrated power compartment, in which a methanol fuel cell power generation system, lithium battery pack, power management and distribution system, methanol fuel storage and supply system, and flight control system are installed.

[0015] Furthermore, the drone body is equipped with heat dissipation fins on its exterior; the heat dissipation fins are an integral structure with the fuselage skin and correspond to the area where the internal methanol fuel cell power generation system is located.

[0016] Compared with the prior art, the present invention has the following beneficial effects: This invention constructs a highly efficient hybrid power system by using a high-energy-density methanol fuel cell as the main power source for cruising flight and a lithium battery as an auxiliary power source. Simultaneously, by optimizing the UAV's structural layout and integrating the fuel cell system, fuel generation system, and UAV fuselage into a single design, the internal space of the UAV can be utilized more effectively. This invention leverages the long-endurance advantage of fuel cells while compensating for the slow dynamic response of lithium batteries, enabling the UAV to cruise for extended periods and handle complex flight missions. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of this utility model.

[0018] Figure 2 This is a connection diagram of the electrical equipment of this utility model.

[0019] The names corresponding to the reference numerals in the attached figures are as follows: 1-UAV body, 2-Methanol fuel cell power generation system, 3-Lithium battery pack, 6-Flight control system, 7-Propulsion motor, 11-Integrated power compartment, 12-Heat dissipation fins, 41-Bidirectional DC / DC converter, 42-Fuel cell controller, 51-Methanol fuel tank, 52-Quick refueling interface, 53-Fuel quantity sensor. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0021] In the description of this utility model, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and 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. Therefore, they should not be construed as limitations on this utility model.

[0022] 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; of course, they can also refer to a mechanical connection or an electrical connection; furthermore, they can refer to a direct connection, an indirect connection through an intermediate medium, or a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0023] like Figures 1-2 As shown, the present invention provides a fixed-wing unmanned aerial vehicle based on a methanol fuel cell, including an unmanned aerial vehicle body 1, and a methanol fuel cell power generation system 2, a lithium battery pack 3, a power management and distribution system, a methanol fuel storage and supply system, and a flight control system 6 integrated inside the unmanned aerial vehicle body 1.

[0024] The methanol fuel cell power generation system 2 and the lithium battery pack 3 constitute a hybrid power system. The methanol fuel cell power generation system 2, with its high energy density, serves as the main power source for cruising, while the lithium battery pack 3, with its high power density, provides peak power and, in the initial stage of UAV takeoff, supplies power to the methanol fuel cell power generation system 2 and its auxiliary equipment before it is fully activated; it can also handle instantaneous high power demands throughout the flight.

[0025] The methanol fuel storage and supply system is connected to the methanol fuel cell power generation system 2 through a supply pipeline, providing methanol fuel to support long-range operation.

[0026] The flight control system 6 is connected to the power management and distribution system. Using the UAV's existing GPS, IMU (Inertial Measurement Unit), airspeed sensor, and other sensors, the flight control system 6 determines the UAV's current flight stage (e.g., takeoff, climb, cruise, maneuvering, landing) in real time. Based on the determined flight stage, it sends energy allocation commands to the power management and distribution system.

[0027] The power management and distribution system is electrically connected to the methanol fuel cell power generation system 2 and the lithium battery pack 3. The power management and distribution system receives energy allocation commands from the flight control system 6. Based on these commands, it coordinates the operation of the two power sources (methanol fuel cell and lithium battery) to trigger the optimal hybrid power allocation scheme. For example, under the economy cruise command: the methanol fuel cell acts as the main power source, and simultaneously charges the lithium battery with a small current to ensure energy reserves. Under the high power command: the methanol fuel cell outputs its rated power, and the lithium battery discharges, together meeting the power demand.

[0028] In some embodiments of this utility model, the methanol fuel cell power generation system 2 is either a direct methanol fuel cell system or a reformed methanol fuel cell system. The direct methanol fuel cell system includes a DMFC stack and a fuel pretreatment unit, which directly electrochemically oxidizes the methanol solution to generate electricity. The reformed methanol fuel cell system includes a methanol reformer, a hydrogen purification device, and a PEMFC stack, which first reforms methanol to produce hydrogen, and then uses the hydrogen to generate electricity in a proton exchange membrane fuel cell.

[0029] In some embodiments of this invention, the flight control system 6 employs a flight control computer, preferably an HPM6750 or an STM32H743VIT6, which connects to various high-precision sensors integrated on the UAV (inertial measurement unit, GPS, barometer, airspeed sensor, etc.). The HPM6750 or STM32H743VIT6 flight control computer has an internal mapping table. Based on this table, it immediately generates corresponding energy allocation commands according to the current flight phase. These commands are encapsulated into data frames conforming to the CAN bus protocol and transmitted in real-time to the fuel cell controller 42 in the power management and distribution system via the CAN bus.

[0030] In some embodiments of this utility model, the power management and distribution system includes a bidirectional DC / DC converter 41 and a fuel cell controller 42. Through the coordinated operation of the bidirectional DC / DC converter 41 and the fuel cell controller 42, intelligent coordinated management of the methanol fuel cell power generation system 2 and the lithium battery pack 3 is achieved. The bidirectional DC / DC converter 41 is connected between the lithium battery pack 3 and the DC bus. The fuel cell controller 42 establishes bidirectional communication connections with the bidirectional DC / DC converter 41, the methanol fuel cell power generation system 2, the lithium battery pack, and the flight control system 6 via a communication bus. The DC bus serves as the power hub of the system, with input terminals including a first input terminal and a second input terminal. The first input terminal is directly connected to the positive and negative power output terminals of the methanol fuel cell power generation system 2, and the second input terminal is directly connected to the high-voltage side port of the bidirectional DC / DC converter 41. Output terminals include a first output terminal and a second output terminal. The first output terminal is directly connected to the DC power input terminal of the propulsion motor 8, and the second output terminal is directly connected to the power input terminals of all other airborne equipment (such as the flight control system, servos, mission payloads, etc.). All power generation units supply energy to the DC bus directly or indirectly; all electrical loads obtain energy directly from the DC bus.

[0031] Preferably, the fuel cell controller 42 employs an embedded microcontroller, preferably a GD32F103C8T6 or an APM32F103C8T6, which internally incorporates an existing energy management algorithm based on flight status. Its coordinated management strategy is specifically manifested in the precise control of the operating mode of the bidirectional DC / DC converter 41 and the dynamic adjustment of the output power of the methanol fuel cell power generation system 2. During takeoff and high-maneuverability phases: When the flight control system 6 issues an energy distribution command requiring peak power, the fuel cell controller 42 immediately sends a discharge command to the bidirectional DC / DC converter 41. The bidirectional DC / DC converter 41 then operates in boost mode, raising the voltage of the lithium battery pack 3 to the DC bus voltage level, and instantaneously injecting the energy stored in the lithium battery pack 3 into the bus. This energy is then added to the base power output of the methanol fuel cell power generation system 2 to meet the total load demand. This process compensates for the slow dynamic response of the fuel cell.

[0032] During the cruise phase: The fuel cell controller 42 sets the methanol fuel cell power generation system 2 as the main power source, controlling its stable output of cruise power. Simultaneously, it sends a charging command to the bidirectional DC / DC converter 41. The bidirectional DC / DC converter 41 then operates in buck mode, reducing the higher voltage on the DC bus and charging the lithium battery pack 3 with a preset safe current. This charging is preferably trickle charging: maintaining the state of charge of the lithium battery pack 3 within a preset optimal range (e.g., 60%-80%), ensuring it is always ready for the next peak power demand, thus achieving energy recycling and storage.

[0033] In some embodiments of this utility model, the methanol fuel storage and supply system includes one or more methanol fuel tanks 51, which are connected to the methanol fuel cell power generation system 2 via supply pipelines. Preferably, the methanol fuel tanks 51 are manufactured using a carbon fiber composite material through a winding molding process. This material is lightweight, resistant to methanol corrosion, and has high strength, effectively improving the system's energy density ratio. The methanol fuel tanks 51 are connected to the fuel inlet of the methanol fuel cell power generation system 2 via flexible supply pipelines made of polytetrafluoroethylene (PTFE). This material is chemically stable and can withstand methanol swelling. The methanol fuel storage and supply system is also equipped with a small, high-efficiency micro-fuel pump (such as a diaphragm pump) to stably and continuously deliver methanol fuel to the methanol fuel cell power generation system 2. The arrangement of the methanol fuel tanks 51 is a core design element for achieving attitude stability during long-endurance flight. Preferably, two identical fuel tanks are used, symmetrically arranged on both sides of the UAV's longitudinal axis, and located at or ahead of the aircraft's center of gravity. This symmetrical arrangement minimizes pitch-direction center of gravity drift caused by fuel consumption.

[0034] In some embodiments of this invention, the methanol fuel storage and supply system also includes a quick-fill interface 52 and a fuel quantity sensor 53. The quick-fill interface 52 is located in an easily accessible position on the top or side of the fuselage and features splash protection and a self-sealing function. This interface connects to the methanol fuel tank 51 via a filling pipe, allowing ground crew to quickly refuel during mission breaks, typically within minutes, far more efficient than battery charging. Each methanol fuel tank 51 integrates a fuel quantity sensor 53, which employs any of the following: a magnetostrictive level sensor, a capacitive level sensor, a float-type level sensor, or a Coriolis mass flow meter, to monitor the volumetric or mass remaining fuel quantity in real time. The fuel quantity data monitored by the fuel quantity sensor 53 is transmitted via cable to the flight control system 6, providing crucial data for mission planning, remaining flight time calculation, and low fuel warnings.

[0035] In some embodiments of this utility model, the UAV body 1 adopts a blended wing-body structure. The blended wing-body structure not only provides excellent aerodynamic efficiency and reduces flight drag, but more importantly, its wide and flat central fuselage provides a continuous and ample internal space. This creates conditions for accommodating large-volume components such as irregularly shaped fuel cell stacks and fuel tanks, which is impossible with traditional beam-structure UAVs. An integrated power compartment 11 is located inside the central fuselage of the blended wing-body structure. The methanol fuel cell power generation system 2, lithium battery pack 3, power management and distribution system, methanol fuel storage and supply system, and flight control system 6 are installed within the integrated power compartment 11. The flight control system 6 is installed in the forward region, where vibrations during flight are relatively low, and communication and sensing antennas are easily deployed, providing a stable and reliable working environment for the flight control computer. The lithium battery pack 3, bidirectional DC / DC converter 41, and methanol fuel tank 51 are compactly arranged in the central core region. Placing the lithium battery pack 3 and the bidirectional DC / DC converter 41, which serves as the main power conversion unit, close together greatly shortens the high-current transmission path, reduces power loss, and improves system response speed. Meanwhile, by concentrating the fuel tank 51 and lithium battery pack 3, the two major counterweight components, near the aircraft's center of gravity, the range of changes in the overall center of gravity can be effectively limited and controlled, ensuring flight attitude stability. The methanol fuel cell power generation system 2 and fuel cell controller 42 are located at the rear. Positioning the fuel cell system at the rear allows its heat-generating components to be closer to the tail. Simultaneously, the proximity of the fuel cell controller 42 and fuel cell power generation system 2 ensures the reliability and real-time performance of control signal transmission. Through the coordinated design of the blended wing-body structure and the internal integrated power cabin, the UAV body 1 of this invention successfully and efficiently encapsulates a complex methanol fuel cell hybrid power system, achieving ultra-long endurance while ensuring excellent aerodynamic performance, structural efficiency, and flight stability.

[0036] In some embodiments of this invention, the exterior of the UAV body 1 is provided with an integrally formed heat dissipation fin 12. Specifically, the heat dissipation fin 12 and the fuselage skin are a co-cured integral structure. Its position, geometry, and heat dissipation area on the outer surface are precisely designed according to the internal heat source distribution to ensure that it is spatially aligned with the core heat-generating area (e.g., fuel cell stack) of the methanol fuel cell power generation system 2 in the internal integrated power compartment. This layout establishes an efficient heat conduction path from the internal heat-generating core to the external environment. Waste heat generated during fuel cell operation is transferred to the fuselage skin via the mounting bracket and air convection within the compartment, using the shortest path, and is ultimately dissipated into the environment through the external heat dissipation fin 12. It cleverly utilizes the inherent oncoming airflow during UAV flight as a cooling medium. By significantly increasing the contact surface area with the airflow, the heat dissipation fin 12 greatly enhances the heat exchange efficiency, achieving zero-power forced air cooling based on flight airspeed. This integrated heat dissipation structure successfully eliminates the need for heavy, power-consuming active cooling fans and separate metal heat sinks commonly found in traditional thermal management solutions. This significantly reduces the weight, complexity, and power consumption of the entire power system, directly contributing to improving the drone's endurance and reliability.

[0037] The long-endurance fixed-wing UAV in this embodiment is made of carbon fiber composite material and has a blended wing-body configuration to provide a larger internal volume and excellent aerodynamic performance.

[0038] In the middle of the fuselage, there is an integrated power compartment. Inside the compartment is a reformed methanol fuel cell system with a rated power of 800W. A fuel cell controller is installed at the rear of the compartment, and a 10Ah lithium battery pack is installed at the front of the fuselage. A bidirectional DC / DC converter is located near the lithium battery pack. At the fuselage's center of gravity, symmetrically arranged on either side are methanol fuel tanks with a total volume of 3 liters, storing a 50% methanol-water solution.

[0039] When the drone takes off, the flight control system commands the power management and distribution system to be powered entirely by the lithium battery pack to meet the high power requirements of the propulsion motor. At the same time, the reformed methanol fuel cell system starts up.

[0040] During the ramp-up phase, the lithium battery pack still bears the main load, and the reformed methanol fuel cell system has started up and begun to output power.

[0041] Once the cruise altitude is reached, the fuel cell controller controls the reformed methanol fuel cell system to output a stable power of approximately 800W, and charges the lithium battery pack with a power of approximately 100W-200W through a bidirectional DC / DC converter, maintaining its SOC between 60% and 80%.

[0042] If the drone needs to accelerate or climb, the power demand increases instantly to 2000W. The fuel cell controller instructs the lithium battery pack to discharge through the bidirectional DC / DC converter, providing 1200W of power together with the reformed methanol fuel cell system.

[0043] Externally, corresponding to the internal fuel cell stack, molded aluminum alloy heat dissipation fins are combined with carbon fiber skin to efficiently cool the fuel cell system using high-speed airflow. A quick-fill port is located on the top of the fuselage, allowing ground personnel to quickly refuel with methanol during mission breaks. A fuel level sensor transmits real-time fuel data to the ground station via the flight control system and data link.

[0044] Through the above design, the UAV in this embodiment can achieve a continuous flight time of more than 10 hours when carrying a 1kg mission payload.

[0045] The direct methanol fuel cell system or reformed methanol fuel cell system, lithium battery pack, STM32H743VIT6 or HPM6750, GD32F103C8T6 or APM32F103C8T6, bidirectional DC / DC converter, magnetostrictive level sensor, capacitive level sensor, float-type level sensor, or Coriolis mass flow meter used in this invention are all existing known electrical devices, and all can be directly purchased and used on the market. Their structure, circuit, and control principle are all existing known technologies. Therefore, the structure, circuit, and control principle of the direct methanol fuel cell system or reformed methanol fuel cell system, lithium battery pack, STM32H743VIT6 or HPM6750, GD32F103C8T6 or APM32F103C8T6, bidirectional DC / DC converter, magnetostrictive level sensor, capacitive level sensor, float-type level sensor, or Coriolis mass flow meter will not be described in detail here.

[0046] Finally, it should be noted that the above embodiments are merely preferred embodiments of this utility model used to illustrate the technical solutions of this utility model, and are not intended to limit it, nor are they intended to limit the patent scope of this utility model. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model. That is to say, any changes or refinements made to the main design concept and spirit of this utility model that are not of substantial significance, but whose technical problems are still consistent with those of this utility model, should be included within the protection scope of this utility model. In addition, the direct or indirect application of the technical solutions of this utility model to other related technical fields are similarly included within the patent protection scope of this utility model.

Claims

1. A fixed-wing unmanned aerial vehicle based on a methanol fuel cell, characterized in that, The system includes a UAV body (1), a methanol fuel cell power generation system (2) integrated inside the UAV body (1) as the main power source for the UAV, and a lithium battery pack (3) as the auxiliary power source for the UAV, a power management and distribution system connected to the methanol fuel cell power generation system (2) and the lithium battery pack (3), a methanol fuel storage and supply system connected to the methanol fuel cell power generation system (2) for supplying fuel to the methanol fuel cell power generation system (2), and a flight control system (6) connected to the power management and distribution system; the flight control system (6) adopts an HPM6750 flight control computer.

2. The fixed-wing unmanned aerial vehicle based on a methanol fuel cell according to claim 1, characterized in that, The methanol fuel cell power generation system (2) is either a direct methanol fuel cell system or a reformed methanol fuel cell system.

3. A fixed-wing unmanned aerial vehicle based on a methanol fuel cell according to claim 1, characterized in that, The input end of the power management and distribution system is connected to the methanol fuel cell power generation system (2) and the lithium battery pack (3), and the output end is connected to the DC bus.

4. A fixed-wing unmanned aerial vehicle based on a methanol fuel cell according to claim 3, characterized in that, The power management and distribution system includes a bidirectional DC / DC converter (41) and a fuel cell controller (42); the bidirectional DC / DC converter (41) is connected between the lithium battery pack (3) and the DC bus; the fuel cell controller (42) is connected to the bidirectional DC / DC converter (41), the methanol fuel cell power generation system (2), the lithium battery pack (3) and the flight control system (6) via a communication bus.

5. A fixed-wing unmanned aerial vehicle based on a methanol fuel cell according to claim 4, characterized in that, The fuel cell controller (42) uses an embedded microcontroller.

6. A fixed-wing unmanned aerial vehicle based on a methanol fuel cell according to claim 1, characterized in that, The methanol fuel storage and supply system includes one or more methanol fuel tanks (51), which are connected to the methanol fuel cell power generation system (2) via supply pipelines; the methanol fuel tanks (51) are symmetrically arranged at the center of gravity of the fuselage.

7. A fixed-wing unmanned aerial vehicle based on a methanol fuel cell according to claim 6, characterized in that, The methanol fuel storage and supply system also includes a quick refueling interface (52) and a fuel quantity sensor (53); the quick refueling interface (52) is located on the side of the fuselage and is connected to the methanol fuel tank (51) via a refueling pipeline; the fuel quantity sensor (53) is integrated inside the methanol fuel tank (51) and is connected to the flight control system (6).

8. A fixed-wing unmanned aerial vehicle based on a methanol fuel cell according to claim 1, characterized in that, The UAV body (1) adopts a blended wing-body structure; an integrated power compartment (11) is located inside the central fuselage of the blended wing-body, and a methanol fuel cell power generation system (2), a lithium battery pack (3), a power management and distribution system, a methanol fuel storage and supply system and a flight control system (6) are installed in the integrated power compartment (11).

9. A fixed-wing unmanned aerial vehicle based on a methanol fuel cell according to claim 1, characterized in that, The drone body (1) is provided with heat dissipation fins (12) on the outside; the heat dissipation fins (12) are integrated with the fuselage skin and correspond to the arrangement area of ​​the internal methanol fuel cell power generation system (2).

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