Modular drone and flight module

Abstract

This invention discloses a modular unmanned aerial vehicle (UAV) and its flight module, relating to the field of UAV technology, to solve the problems of large size, inconvenient transportation, and difficulty in flexible configuration adjustment. The modular UAV includes multiple flight modules, which are connected by a connecting structure to form a multi-module assembly. Each flight module includes a fuselage, rotor, engine, and management platform. The management platform controls the flight of its corresponding flight module. When multiple flight modules are assembled, the management platforms are interconnected, and one management platform is designated as the master control platform. The master control platform receives external flight commands and generates coordinated control commands, which are then distributed to the other management platforms to control the flight modules to fly collaboratively. This invention provides a modular UAV and its flight module to address the problems of existing heavy-load UAVs, such as difficulties in transportation and deployment due to their integrated structure, poor mission adaptability, and insufficient reliability due to the lack of a deep collaborative control mechanism.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a modular UAV and its flight module. Background Technology

[0002] With the widespread application of drone technology in logistics, emergency rescue, and special operations, the requirements for its payload capacity, mission adaptability, and deployment flexibility are increasing. However, most existing heavy-duty drones have very limited payload capacity and can only be used for transporting small items. In recent years, with the rapid development of the drone industry, the demand for higher payload capacity has become more urgent, thus creating a need for drones with greater payload capabilities.

[0003] Existing large heavy-duty drones typically adopt an integrated design, which has problems such as large size, inconvenient transportation, and difficulty in flexibly adjusting configuration according to mission requirements, and cannot meet the complex and ever-changing high-load operation requirements. Summary of the Invention

[0004] The purpose of this invention is to provide a modular unmanned aerial vehicle (UAV) and flight module to solve the problems of transportation and deployment difficulties, poor mission adaptability, and insufficient reliability of existing heavy-duty UAVs due to their integrated structure and lack of deep collaborative control mechanisms.

[0005] To achieve the above objectives, in a first aspect, the present invention provides a modular unmanned aerial vehicle (UAV) comprising multiple flight modules, which are spliced ​​together by detachable connection structures to form a multi-module assembly. Each flight module includes a fuselage, a rotor, an engine, and a management platform. The rotor is disposed on the fuselage; the engine is disposed within the fuselage; and the management platform is disposed within the fuselage for controlling the flight of the corresponding flight module. When multiple flight modules are spliced ​​together, the management platforms are interconnected, and one of the management platforms is designated as the master control platform. The master control platform is used to receive external flight commands and generate coordinated control commands to distribute to the other management platforms to control the flight modules to perform coordinated flight.

[0006] Furthermore, the rotors of the multiple flight modules are staggered vertically in the overall layout after assembly.

[0007] Furthermore, the flight module also includes a composite heat dissipation structure, which includes a liquid-cooled radiator and an air-cooled auxiliary heat dissipation structure. The liquid-cooled radiator is connected to the engine's coolant circuit; the air-cooled auxiliary heat dissipation structure is located in the airflow path of the liquid-cooled radiator and dissipates heat from the liquid-cooled radiator through the airflow generated by the impact wind during flight and the rotation of the rotor.

[0008] Furthermore, the flight module also includes a transmission mechanism for transmitting the engine's power to the rotor. The transmission mechanism includes a transmission disc, a driven disc, and a flexible belt fitted on the transmission disc and the driven disc. The transmission disc is connected to the output end of the engine, and the driven disc is connected to the rotor. The transmission mechanism also includes an automatic tensioning mechanism for maintaining the tension of the flexible belt.

[0009] Furthermore, the flight module also includes a retractable frame located under the fuselage of the flight module for adjusting the cargo space according to the cargo size; and / or, the flight module also includes a sling mount located at the bottom of the fuselage for quickly installing or replacing mission attachments.

[0010] Furthermore, the modular drone also includes a parachute, which is mounted on the fuselage of the flight module; when the management platform detects a serious malfunction or receives an emergency command, it controls the deployment of the parachute to achieve a safe landing.

[0011] Furthermore, the flight module includes an intelligent actuator, which is located at the rotor hub. The intelligent actuator is connected to the management platform and independently controls the rotor blade angle via electrical signals.

[0012] Furthermore, the modular drone also includes at least one multi-output fuel tank, located inside the fuselage of the flight module. The fuel tank has multiple fuel output ports, which can be used to select independent fuel supply or shared fuel when multiple flight modules are spliced ​​together.

[0013] Secondly, the present invention also provides a flight module for use in the modular drone described above.

[0014] Furthermore, the flight module also includes a detachable tail fin, which is installed on the fuselage of the flight module when the flight module is flying alone, and removed when the flight module is spliced ​​with other flight modules.

[0015] As can be seen from the above, the modular UAV and flight module provided in this application have the following beneficial effects: 1. Flexible transportation and deployment, adjustable payload: This invention designs a large drone as an assembly of multiple flight modules. During transportation or storage, it can be disassembled into independent modules, greatly reducing the size of individual components and the difficulty of transportation. In practical applications, the number of modules can be flexibly increased or decreased like building blocks according to the payload required for the mission, achieving linear expansion of payload capacity and effectively solving the problems of inconvenient transportation and rigid configuration of traditional integrated heavy-duty drones.

[0016] 2. Intelligent and collaborative flight control for high system reliability: Each flight module is equipped with an independent management platform. When the modules are connected, these management platforms network together, and a master control platform is designated to coordinate the actions of all modules. This distributed collaborative control method enables multiple modules to fly stably and precisely like a single aircraft. Even if the engine or flight control system of a certain module fails, the master control platform can immediately adjust the power output of other modules to maintain the overall flight attitude and safety, achieving high-reliability system safety.

[0017] 3. Flight Efficiency and Power Performance Optimization: By designing the rotors of adjacent modules in a staggered vertical layout, airflow interference between multi-rotors is significantly reduced, thereby improving overall aerodynamic efficiency and achieving greater effective lift with the same power consumption. Simultaneously, a composite cooling system, primarily liquid-cooled and supplemented by air-cooled for enhanced heat dissipation, fully utilizes natural airflow during flight to efficiently cool the engine, ensuring continuous and stable power system output under heavy load conditions. The flexible belt drive mechanism also effectively absorbs engine vibration, resulting in smoother and quieter flight.

[0018] 4. Strong mission adaptability and guaranteed safety: The retractable frame at the bottom of the module can accommodate cargo of different sizes, while the standardized mounting interface allows for quick replacement of various mission payloads such as cargo equipment, fire-fighting equipment, and surveying equipment, achieving "one machine for multiple uses". The modular UAV integrates a parachute, which is intelligently monitored by the management platform that serves as the main control platform. It can automatically trigger deployment when a serious fault is detected, providing a final layer of safety protection for the expensive flight module and critical payload, and significantly reducing the risk of crash losses.

[0019] 5. Convenient Energy Management and Maintenance: The module's built-in multi-output fuel tank supports both interconnected and shared fuel lines and independent fuel supply modes. Users can flexibly choose according to the mission's requirements for range and reliability. For example, for shorter ranges, the modular UAV can be equipped with only one fuel tank, with the engines of multiple flight modules connected to this tank; or, for longer ranges, each flight module can be equipped with one fuel tank, with each tank independently supplying fuel to the engine of that flight module; or, each flight module can be equipped with multiple fuel tanks, with each tank independently supplying fuel to the engines of at least two flight modules. The specific number of fuel tanks can be installed according to actual mission requirements. This configuration improves the flexibility of energy utilization. In addition, the flight module itself, as a complete and collaborative standard unit, facilitates mass production, individual replacement, and maintenance, reducing the total life-cycle cost. The detachable tail fin design allows a single module to achieve good flight stability even when independently performing lightweight missions. Attached Figure Description

[0020] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings: Figure 1 A schematic diagram of a modular unmanned aerial vehicle (UAV) provided for an embodiment of the present invention; Figure 2 A schematic diagram of a flight module provided for an embodiment of the present invention; Figure 3 A schematic diagram of another modular unmanned aerial vehicle provided in an embodiment of the present invention; Figure 4 A schematic diagram of yet another modular unmanned aerial vehicle provided in an embodiment of the present invention; Figure 5 A schematic diagram of yet another modular unmanned aerial vehicle provided in an embodiment of the present invention; Figure 6 A schematic diagram of yet another modular unmanned aerial vehicle provided in an embodiment of the present invention; Figure 7 A schematic diagram of yet another modular unmanned aerial vehicle provided in an embodiment of the present invention; Figure 8 A schematic diagram of another flight module provided in an embodiment of the present invention; Figure 9 A schematic diagram of yet another flight module provided in an embodiment of the present invention; Figure 10 A schematic diagram of yet another flight module provided in an embodiment of the present invention; Figure 11 A schematic diagram of yet another flight module provided in an embodiment of the present invention; Figure 12 This is a schematic diagram of a hanging interface and winch combination provided in an embodiment of the present invention; Figure 13 A schematic diagram of yet another modular unmanned aerial vehicle provided in an embodiment of the present invention; Figure 14 A schematic diagram of a mechanical linkage control mechanism provided in an embodiment of the present invention; Figure 15 A schematic diagram of a multi-outlet fuel tank provided in an embodiment of the present invention; Figure 16 This is a schematic diagram of another flight module provided in an embodiment of the present invention.

[0021] Reference numerals: 1-Flight module; 11-Fuselage; 12-Rotor; 13-Engine; 14-Management platform; 15-Composite heat dissipation structure; 151-Liquid-cooled radiator; 152-Air-cooled auxiliary heat dissipation structure; 16-Transmission mechanism; 161-Transmission disc; 162-Driven disc; 163-Flexible belt; 164-Automatic tensioning mechanism; 17-Retractable frame; 18-Hosting interface; 19-Parachute; 20-Windlass; 21-Mechanical linkage control mechanism; 211-Mechanical swashplate; 212-Push-pull rod; 213-Propeller hub; 22-Detachable tail fin; 23-Multi-outlet fuel tank; 231-Fuel outlet; 2-Connection structure. Detailed Implementation

[0022] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.

[0023] It should be noted that when a component is referred to as "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0024] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. "Several" means one or more, unless otherwise explicitly specified.

[0025] In the description of this invention, it should be understood that the terms "upper" and "lower" 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 invention 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 limiting this invention.

[0026] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the term "connection" should be interpreted broadly. For example, it can refer to a fixed connection, a detachable connection, or an integral connection; it can refer to a direct connection or an indirect connection through an intermediate medium; it can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0027] With the widespread application of drone technology in logistics, emergency rescue, and special operations, the requirements for its payload capacity, mission adaptability, and deployment flexibility are increasing. However, existing large, heavy-duty drones typically employ an integrated design, which suffers from problems such as bulkiness, inconvenient transportation, and difficulty in flexibly adjusting configurations according to mission requirements, failing to meet the complex and ever-changing demands of high-load operations. In particular, the integrated structure lacks flexibility when facing transportation tasks of varying tonnages, and its inherent "single point of failure" risk also restricts the reliability of its application in critical missions.

[0028] To solve the above problems, such as Figures 1 to 16 As shown, this embodiment of the invention provides a modular unmanned aerial vehicle (UAV), including multiple flight modules 1. The flight modules 1 are spliced ​​together by detachable connecting structures 2 to form a multi-module assembly; as shown... Figure 2 As shown, each flight module 1 includes a fuselage 11, a rotor 12, an engine 13, and a management platform 14. The rotor 12 is mounted on the fuselage 11; the engine 13 is located inside the fuselage 11; and the management platform 14 is located inside the fuselage 11 and is used to control the flight of the corresponding flight module 1. When multiple flight modules 1 are connected, the management platforms 14 are interconnected, and one of the management platforms 14 is designated as the master control platform. The master control platform is used to receive external flight commands and generate coordinated control commands to distribute to the other management platforms 14 to control the flight modules 1 to perform coordinated flight.

[0029] After multiple flight modules 1 are assembled, multiple management platforms 14 can be connected via signal lines (not shown in the figure) to form a local control network. Once the network is started, it will automatically elect a master control platform based on a preset algorithm (e.g., based on module serial number, startup order, or signal quality) to be responsible for the flight decision-making and coordination of the entire assembly.

[0030] Through the above structure, firstly, the modular UAV provided in this embodiment of the invention achieves great flexibility in transportation and deployment. Large UAVs can be disassembled into multiple standard-sized flight modules 1 for transportation, effectively solving the problems of land transportation and storage difficulties caused by excessive overall size. In actual operation, users can flexibly combine different numbers of modules according to mission payload requirements, like building blocks, to achieve linear expansion of payload capacity. For example, as... Figure 1As shown, the modular UAV consists of two flight modules 1 combined; or, as... Figure 3 As shown, the modular drone consists of four flight modules 1 combined; or, as... Figure 4 As shown, the modular drone consists of six flight modules 1; or, as... Figure 5 As shown, the modular drone consists of eight flight modules 1; or, as... Figure 6 As shown, the modular UAV consists of 10 flight modules 1. The payload capacity of the modular UAV can range from 600 kg for a two-module UAV to over 3 tons for a ten-module UAV. Secondly, the modular UAV provided in this embodiment of the invention constructs an intelligent collaborative control architecture. The distributed management platform 14, through networking, enables multiple physically independent flight modules 1 to receive commands and fly stably as a whole, solving the problem of multi-unit collaborative control. Finally, the modular UAV provided in this embodiment of the invention achieves highly reliable system security. The failure of any flight module 1 will not lead to overall system failure; the main control platform can dynamically adjust the working status of the remaining modules to maintain basic flight capabilities, significantly improving system security.

[0031] Therefore, this invention designs a large UAV as composed of multiple flight modules 1. During transportation or storage, it can be disassembled into independent modules, greatly reducing the volume of individual components and the difficulty of transportation. In practical applications, the number of modules can be flexibly increased or decreased like building blocks according to the payload required for the mission, achieving linear expansion of payload capacity and adapting to different work requirements. This solves the problems of difficult transportation and deployment and poor mission adaptability caused by the integrated structure of existing heavy-duty UAVs. Each flight module 1 is equipped with an independent management platform 14. When the modules are assembled, these management platforms 14 are networked, and a master control platform is set up to coordinate the actions of all modules. This distributed collaborative control method enables multiple modules to fly stably and accurately like a single aircraft, improving flight reliability. This addresses the reliability issues in some solutions where multiple UAVs combined lack a deep collaborative control mechanism.

[0032] Furthermore, such as Figure 7 As shown, the rotors 12 of multiple flight modules 1 are staggered vertically in the overall layout after assembly. This design ensures that the rotation planes of the rotors 12 of adjacent modules are not at the same height, thus effectively avoiding direct collision and interference of the downwash airflow of the rotors 12. This significantly reduces power loss caused by aerodynamic interference, improves overall aerodynamic efficiency, allows the assembly to achieve greater effective lift with the same power consumption, and enhances flight stability.

[0033] Furthermore, such as Figure 8 As shown, the flight module 1 also includes a composite heat dissipation structure 15, such as... Figure 9As shown, the composite heat dissipation structure 15 includes a liquid-cooled radiator 151 and an air-cooled auxiliary heat dissipation structure 152. The liquid-cooled radiator 151 is connected to the coolant circuit of the engine 13; the air-cooled auxiliary heat dissipation structure 152 is disposed in the airflow path of the liquid-cooled radiator 151, and uses the airflow generated by the impact wind during flight and the rotation of the rotor 12 (such as...) Figure 9 (As indicated by the middle arrow) The liquid-cooled radiator 151 dissipates heat. This solution ensures that the engine 13 can operate stably within the optimal temperature range under continuous heavy load conditions, fundamentally preventing the "thermal decay" phenomenon, extending the life of the engine 13, and ensuring the continuity and reliability of power output.

[0034] Furthermore, such as Figure 8 As shown, flight module 1 also includes a transmission mechanism 16, which transmits power from engine 13 to rotor 12. The transmission mechanism 16 includes a transmission disc 161, a driven disc 162, and a flexible belt 163 fitted onto the transmission disc 161 and driven disc 162. The transmission disc 161 is connected to the output end of engine 13, and the driven disc 162 is connected to rotor 12. The transmission mechanism 16 also includes an automatic tensioning mechanism 164 for maintaining the tension of the flexible belt 163. The flexible belt 163 transmission can efficiently attenuate the torsional vibration of engine 13, reduce flight noise and airframe vibration, and improve flight smoothness. Simultaneously, the belt drive has the characteristic of overload slippage, providing natural overload protection for the transmission system.

[0035] Furthermore, such as Figure 10 As shown, the flight module 1 also includes a retractable frame 17, which is located below the fuselage 11 of the flight module 1 and is used to adjust the cargo space according to the cargo size. This design enables the UAV to accommodate cargo of different sizes, improving the space utilization and mission adaptability of a single flight.

[0036] In some embodiments, such as Figure 11 and Figure 12 As shown, flight module 1 also includes a mounting interface 18, which is located at the bottom of the fuselage 11 of flight module 1 and is used for quick installation or replacement of mission attachments. The standardized mounting interface 18 supports quick connection to various mission modules such as cargo pallets, fire buckets, and inspection equipment, realizing "one machine for multiple uses" and greatly expanding the application scenarios and functional flexibility of UAVs.

[0037] The flight module 1 may also include a winch 20, which has a motor. The hoisting interface 18 can be raised and lowered by the winch 20 to facilitate the hoisting of items by the staff.

[0038] For example, flight module 1 may include a retractable frame 17; or, flight module 1 may include a sling interface 18; or, flight module 1 may include a retractable frame 17 and a sling interface 18.

[0039] Furthermore, such as Figure 13 As shown, the modular UAV also includes a parachute 19, which is mounted on the fuselage 11 of the flight module 1. When the management platform 14 detects a serious malfunction or receives an emergency command, it controls the deployment of the parachute 19 to achieve a safe landing. Equipping each flight module 1 with an independent parachute 19 constitutes ultimate system-level safety redundancy. In the event of an irreversible failure, it can achieve a slow descent to the maximum extent, protecting the expensive flight module 1 and its payload, and significantly reducing the risk of crash and loss.

[0040] In some embodiments, flight module 1 includes intelligent actuators (not shown, obscured in the figure), which are located at the hub 213 of rotor 12. These intelligent actuators are communicatively connected to management platform 14 and independently control the blade angle of rotor 12 via electrical signals. Control commands are converted into digital signals and transmitted to the flight control computer (FCC). The FCC integrates sensor data and the calculated control law to generate commands and sends them to the intelligent actuators integrated into the hub 213 of each rotor 12. Each intelligent actuator is an independent "digital module" with a built-in motor, controller, and feedback sensor, capable of quickly and accurately driving its assigned blade independently. This fly-by-wire flight control method achieves physical separation of power and control, eliminating the complex mechanical swashplate 211 and linkage mechanism. It simplifies the mechanical structure, improves reliability, and allows for more precise and faster pitch control via software.

[0041] In other embodiments, such as Figure 14 As shown, the blade angle control of rotor 12 can also employ a mechanical linkage control mechanism 21. The mechanical linkage control mechanism 21 uses a mechanical swashplate 211, and connected push-pull rods 212 and rotor hub 213 to uniformly change the angle of all blades. This system can also include a hydraulic system to overcome the enormous aerodynamic loads through hydraulic assistance. This solution is robust and can be used in certain operating scenarios with stringent cost or specific reliability requirements.

[0042] Furthermore, such as Figure 1 and Figure 15 As shown, the modular UAV also includes at least one multi-output fuel tank 23, located within the fuselage 11 of the flight module 1. The fuel tank has multiple fuel outlets 231, allowing for independent fuel supply or shared fuel when multiple flight modules 1 are assembled. For example, in short-range missions, only one fuel tank can be used to supply fuel to all modules to reduce weight; in long-range or high-reliability missions, each module can use an independent fuel tank. This design provides a flexible energy management strategy, allowing users to strike a balance between simplifying the system and enhancing redundancy according to mission requirements, improving the economy and adaptability of the entire mission system.

[0043] Engine 13 can use gasoline or methanol fuel, providing more fuel options under different environments and resupply conditions, thus enhancing the UAV's deployment capabilities and mission adaptability in complex environments such as the field and remote areas.

[0044] Furthermore, the fuselage 11 of flight module 1 is manufactured using a composite material of high-strength aerospace aluminum and titanium alloy. Aerospace aluminum provides excellent specific strength, enabling lightweight construction; while titanium alloy offers extremely high strength, fatigue resistance, and corrosion resistance at key load-bearing nodes and connections. This material application minimizes weight while ensuring absolute structural reliability, contributing to increased payload and endurance.

[0045] The modular UAV structural design provided in this invention is based on digital simulation tools such as computational fluid dynamics (CFD) and finite element analysis (FEA). By comprehensively simulating and optimizing the stress, vibration modes, and aerodynamic characteristics of single modules and multi-module combinations under various working conditions, the structural safety, dynamic stability, and aerodynamic efficiency from individual units to the assembly are ensured, fundamentally eliminating the systemic risk of "1+1<2" and achieving the optimal balance between performance and reliability.

[0046] Furthermore, this embodiment of the invention also provides a flight module 1 for use in any of the aforementioned modular unmanned aerial vehicles (UAVs). The flight module 1 includes a fuselage 11, a rotor 12, an engine 13, and a management platform 14; the rotor 12 is mounted on the fuselage 11; the engine 13 is located within the fuselage 11; and the management platform 14 is located within the fuselage 11 and is used to control the flight of the corresponding flight module 1. The flight module 1 itself is a standard unit with complete flight capabilities and an embedded collaborative control management platform 14.

[0047] Furthermore, such as Figure 16 As shown, flight module 1 also includes a detachable tail fin 22. The tail fin is installed on the fuselage 11 of flight module 1 when flight module 1 is flying alone, and is removed when flight module 1 is spliced ​​with other flight modules 1. The tail fin provides the necessary directional and pitch stability for a single module to perform a mission independently, optimizing the single-aircraft flight performance. Removing the tail fin when participating in a combination avoids structural interference and enables the same module to flexibly switch between "independent operation" and "cluster collaboration" modes.

[0048] In the description of the above embodiments, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0049] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A modular unmanned aerial vehicle (UAV), characterized in that, include: Multiple flight modules are connected together by a detachable connection structure to form a multi-module assembly; Each of the flight modules includes: body; A rotor, which is mounted on the fuselage; An engine, which is disposed within the fuselage; A management platform, located inside the fuselage, is used to control the flight of the corresponding flight module; When multiple flight modules are spliced ​​together, the management platforms are interconnected, and one of the management platforms is designated as the master control platform. The master control platform is used to receive external flight commands and generate coordination control commands to distribute to the other management platforms in order to control the flight modules to perform coordinated flight.

2. The modular UAV as described in claim 1, characterized in that, The rotors of the multiple flight modules are staggered vertically in the overall layout after assembly.

3. The modular UAV as described in claim 1, characterized in that, The flight module also includes: The composite heat dissipation structure includes a liquid-cooled radiator and an air-cooled auxiliary heat dissipation structure. The liquid-cooled radiator is connected to the coolant circuit of the engine. The air-cooled auxiliary heat dissipation structure is located in the airflow path of the liquid-cooled radiator and dissipates heat from the liquid-cooled radiator through the impact wind during flight and the airflow generated by the rotation of the rotor.

4. The modular UAV as described in claim 1, characterized in that, The flight module also includes a transmission mechanism for transmitting the power of the engine to the rotor. The transmission mechanism includes a transmission disc, a driven disc, and a flexible belt sleeved on the transmission disc and the driven disc. The transmission disc is connected to the output end of the engine, and the driven disc is connected to the rotor. The transmission mechanism also includes an automatic tensioning mechanism for maintaining the tension of the flexible belt.

5. The modular UAV as described in claim 1, characterized in that, The flight module also includes a retractable frame located below the fuselage of the flight module, which is used to adjust the cargo space according to the cargo size; And / or, the flight module further includes a mounting interface located at the bottom of the flight module fuselage for quick installation or replacement of mission attachments.

6. The modular UAV as described in claim 1, characterized in that, The modular drone also includes a parachute, which is mounted on the fuselage of the flight module; when the management platform detects a serious malfunction or receives an emergency command, it controls the deployment of the parachute to achieve a safe landing.

7. The modular UAV as described in claim 1, characterized in that, The flight module includes an intelligent actuator located at the rotor hub. The intelligent actuator is communicatively connected to the management platform and independently controls the rotor blade angle via electrical signals.

8. The modular UAV as described in claim 1, characterized in that, The modular UAV also includes at least one multi-output fuel tank, which is located inside the fuselage of the flight module. The multi-output fuel tank is provided with multiple fuel output ports, which are used to select independent fuel supply or shared fuel when multiple flight modules are spliced ​​together.

9. A flight module, characterized in that, In a modular UAV as described in any one of claims 1 to 8, the flight module comprises: body; A rotor, which is mounted on the fuselage; An engine, which is disposed within the fuselage; The management platform, located inside the fuselage, is used to control the flight of the corresponding flight module.

10. The flight module as described in claim 9, characterized in that, The flight module also includes a detachable tail fin, which is installed on the fuselage of the flight module when the flight module is flying alone, and removed when the flight module is spliced ​​with other flight modules.

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