Hybrid unmanned aerial vehicle system

Abstract

This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a hybrid power UAV system. The hybrid power UAV system of this invention includes a UAV, a first energy device, and a second energy device. A connecting portion is provided at the bottom of the UAV. The first energy device includes a first housing; the second energy device includes a second housing. Connecting components are respectively provided at the top of the first and second housings, and these connecting components are used to engage with the connecting portion. By using the hybrid power UAV of this technical solution, rapid and stable interchangeability of different power modules on the same UAV is achieved. Users can select the energy device to be mounted according to actual mission requirements, flexibly responding to different application scenarios such as short-range high-frequency operations and long-endurance missions, thereby significantly reducing redundant investment and idle costs, and improving the utilization rate and economy of a single UAV.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, and specifically relates to a hybrid power UAV system. Background Technology

[0002] As the global climate governance process deepens, various industries are accelerating their transformation towards green and low-carbon directions. Simultaneously, the low-altitude economy, as a strategic emerging industry, has ushered in unprecedented development opportunities. Against this backdrop, new energy drone technology has developed rapidly, becoming one of the important directions for energy conservation and emission reduction in the aviation field. Currently, new energy drones mainly form two technological routes: one is electric drones based on pure electric power (including rechargeable and battery-swapping types), which have advantages such as simple structure, mature control, and zero emissions, and have already achieved large-scale application in multiple industries; the other is based on hydrogen fuel cell power systems, which, with the high energy density and long endurance of hydrogen fuel, demonstrate significant advantages in long-endurance and heavy-load application scenarios.

[0003] However, both types of power systems face their own bottlenecks in widespread application. Pure electric drones are limited by battery energy density, resulting in generally short flight times that cannot meet the demands of long-duration operations. While hydrogen fuel cell drones offer longer flight times, the high cost of their primary energy source makes the overall cost significantly higher than comparable electric drones, becoming a major obstacle to their large-scale commercial application. More importantly, in existing technologies, pure electric and hydrogen fuel cell drones are independent and incompatible in terms of their power system architecture. Users who wish to flexibly switch between power modes for different mission scenarios (such as short-distance, high-frequency operations or long-endurance missions) often need to purchase both types of drones simultaneously, leading to redundant resource investment, high operating costs, and low equipment utilization. Currently, there is a lack of a system solution that allows for the interchangeability and resource sharing of pure electric and hydrogen fuel cell power modules on the same drone platform, thus limiting the overall economic efficiency of new energy drones.

[0004] Therefore, there is an urgent need to provide a drone system that is compatible with multiple power modules, so that the drone can flexibly change the power module according to the actual mission requirements and realize the on-demand switching of power form. Summary of the Invention

[0005] The purpose of this invention is to provide a hybrid-powered unmanned aerial vehicle (UAV) system capable of switching power modes on demand. This purpose is achieved through the following technical solution: A first aspect of the present invention provides a hybrid unmanned aerial vehicle (UAV) system, comprising: The drone has a connecting part at its bottom; A first energy device, the first energy device including a first housing; A second energy device, the second energy device including a second housing; The top of the first housing and the second housing are respectively provided with connecting components, which are used to engage with the connecting part.

[0006] By incorporating a universal connector on the bottom of the drone and connecting components on the top of the first and second energy devices for easy connection, the design enables rapid and stable interchangeability of different power modules on the same drone. This design significantly reduces the user's overall operating costs. Users no longer need to purchase two separate drone systems; they only need one drone and can flexibly handle different application scenarios, such as short-range, high-frequency operations and long-endurance missions, by selecting the appropriate energy device based on actual mission requirements. This greatly reduces redundant investment and idle costs, and improves the utilization rate and economic efficiency of a single drone.

[0007] In addition, the hybrid unmanned aerial vehicle system of the present invention may also have the following additional technical features: In some embodiments of the present invention, the connecting part is provided with a locking hole, and the connecting assembly includes a guide post and a locking hook. The locking hook is connected to the guide post, and when the guide post and the locking hook are inserted into the locking hole, the locking hook abuts against the connecting part.

[0008] In some embodiments of the present invention, the connecting part has a cavity inside, one end of the hook is connected to the cavity wall, and the other end of the hook extends out of the cavity.

[0009] In some embodiments of the present invention, the drone includes a positioning shell having an opening, the connecting portion being connected to the cavity wall of the opening, and the opening being used for insertion with the first shell or the second shell.

[0010] In some embodiments of the present invention, the tops of the first housing and the second housing are respectively provided with conductive terminals, and the interior of the opening is provided with a conductive interface, wherein the conductive terminals are used to be plugged into the conductive interface.

[0011] In some embodiments of the present invention, the first energy device is a hydrogen fuel cell device, and the second energy device is a power battery device.

[0012] In some embodiments of the present invention, the top of the first housing is provided with a first groove 211a, and the guide post on the first housing is disposed inside the first groove 211a; the top of the second housing is provided with a second groove 221a, and the guide post on the second housing is disposed inside the second groove 221a.

[0013] In some embodiments of the present invention, the hybrid unmanned aerial vehicle system further includes a transport device, which includes rollers, a base, a lifting assembly, and a support platform. The rollers are connected to the bottom of the base, and the support platform is connected to the base via the lifting assembly. The support platform is used to place the first energy device or the second energy device.

[0014] In some embodiments of the present invention, the lifting assembly includes a telescopic bracket and a driving component. The bottom of the telescopic bracket is connected to the base, the top of the telescopic bracket is connected to the support platform, the driving component is disposed inside the telescopic bracket, the fixed end of the driving component is connected to the base, and the output end of the driving component is connected to the support platform.

[0015] In some embodiments of the present invention, a first positioning part is provided on the support platform, and a second positioning part is provided on the top of the first housing and the second housing, respectively, and the first positioning part and the second positioning part are positioned and inserted together. Attached Figure Description

[0016] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 A schematic diagram of the structure of a hybrid unmanned aerial vehicle system according to an embodiment of the present invention is shown. Figure 2 A schematic diagram of the structure of a drone according to an embodiment of the present invention is shown; Figure 3 yes Figure 2 A magnified view of a section at point A in the middle; Figure 4 A schematic diagram of the structure of the connection component according to an embodiment of the present invention is shown. Figure 5 A schematic diagram of the structure of a transportation device according to an embodiment of the present invention is shown. Figure 6 A schematic diagram of a partial structure of a first energy device according to an embodiment of the present invention is shown at a certain angle. Figure 7 A schematic diagram of a partial structure of a first energy device according to an embodiment of the present invention is shown from another angle.

[0017] The labels in the attached diagram are as follows: 100. Unmanned aerial vehicle (UAV); 110. Connecting part; 111. Clip; 120. Positioning shell; 121. Opening mouth; 130. Bracket; 210. First energy device; 211. First housing; 211a. First recess; 212. Power battery system; 213. Hydrogen storage system; 214. Thermal management system; 215. Circuit connector; 216. Hydrogen fuel reactor system; 217. Frame system; 218. Silencer assembly; 220. Second energy device; 221. Second housing; 221a. Second groove; 230. Connecting assembly; 231. Guide post; 232. Cavity; 233. Hook; 240. Conductive connector; 300. Transport equipment; 310. Rollers; 320. Base; 330. Lifting assembly; 340. Support platform; 341. First positioning part. Detailed Implementation

[0018] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0019] It should be understood that the terminology used herein is for the purpose of describing particular exemplary embodiments only and is not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “described” as used herein may also include the plural forms. The terms “comprising,” “including,” “containing,” and “having” are inclusive and therefore indicate the presence of the stated features, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, elements, components, and / or combinations thereof. The method steps, processes, and operations described herein are not construed as requiring them to be performed in a particular order described or illustrated unless the order of performance is explicitly indicated. It should also be understood that additional or alternative steps may be used.

[0020] Although terms such as first, second, third, etc., may be used in this document to describe multiple elements, components, regions, layers, and / or segments, these elements, components, regions, layers, and / or segments should not be limited by these terms. These terms may be used only to distinguish one element, component, region, layer, or segment from another. Unless the context clearly indicates otherwise, terms such as "first," "second," and other numerical terms used herein do not imply order or sequence. Therefore, the first element, component, region, layer, or segment discussed below may be referred to as the second element, component, region, layer, or segment without departing from the teachings of the exemplary embodiments.

[0021] For ease of description, spatial relative terms may be used in the text to describe the relationship of one element or feature relative to another element or feature, as shown in the figure. These relative terms include, for example, "inside," "outside," "middle," "outer," "below," "below," "above," "over," etc. Such spatial relative terms are intended to include different orientations of the device in use or operation, other than those depicted in the figure. For example, if the device in the figure is flipped, an element described as "below other elements or features" or "below other elements or features" would subsequently be oriented "above other elements or features" or "above other elements or features." Therefore, the example term "below" can include both upper and lower orientations.

[0022] Figure 1 A schematic diagram of the structure of a hybrid unmanned aerial vehicle system according to an embodiment of the present invention is shown. Figure 2 A schematic diagram of the structure of a drone 100 according to an embodiment of the present invention is shown. Figure 3 yes Figure 2 A magnified view of a portion of point A in the middle. Figure 4 A schematic diagram of the structure of the connection component 230 according to an embodiment of the present invention is shown. Figures 1 to 4 As shown, the present invention proposes a hybrid unmanned aerial vehicle (UAV) system, including a UAV 100, a first energy device 210, and a second energy device 220; a connecting part 110 is provided at the bottom of the UAV 100; the first energy device 210 includes a first housing 211; the second energy device 220 includes a second housing 221; connecting components 230 are respectively provided at the top of the first housing 211 and the second housing 221, and the connecting components 230 are used to engage with the connecting part 110.

[0023] By incorporating a universal connector 110 at the bottom of the drone 100, and connecting components 230 on the tops of the first energy device 210 and the second energy device 220 respectively, which can be connected to the connector, rapid and stable interchangeability of different power modules is achieved on the same drone 100. This design significantly reduces the user's overall operating costs. Users do not need to purchase two independent drone systems simultaneously; they only need to equip themselves with one drone 100 and select the appropriate power device according to actual mission requirements. This allows them to flexibly handle different application scenarios, such as short-distance high-frequency operations and long-endurance missions, thereby greatly reducing redundant investment and idle costs, and improving the utilization rate and economy of a single drone 100.

[0024] In this embodiment, both the first housing 211 and the second housing 221 are generally cuboid in shape, with a square cross-section in the horizontal direction. Each housing is provided with four connecting components 230, located at the four corners of the housing. In other embodiments, the horizontal cross-section of the housing can be circular, oblong, or cross-shaped, etc., and the number of connecting components 230 can be one, two, or three, depending on the specific application requirements. Understandably, the number and position of the connecting parts 110 on the UAV 100 are coordinated with the number and position of the connecting components 230 on the housing.

[0025] Furthermore, the connecting part 110 is provided with a locking hole 111, and the connecting component 230 includes a guide post 231 and a hook 233. The hook 233 is connected to the guide post 231. When the guide post 231 and the hook 233 are inserted into the locking hole 111, the hook 233 abuts against the connecting part 110.

[0026] The guide post 231, in conjunction with the locking hole 111, enables rapid guidance and positioning of the UAV 100 and energy equipment during installation, ensuring accurate and smooth insertion and preventing operational jamming or interface damage due to alignment deviations. After being fully inserted into the locking hole 111, the hook 233 forms a locking contact with the connecting part 110, relying on a mechanical self-locking structure to ensure a stable connection between the energy equipment and the UAV 100 during flight, preventing accidental loosening due to vibration. Simultaneously, this locking structure facilitates easy assembly and disassembly, allowing for rapid replacement of the energy module without additional tools, significantly improving replacement efficiency. Optionally, the top of the guide post 231 can be designed as a cone structure, meaning the outer diameter of the top of the guide post 231 is smaller than the diameter of the locking hole 111. This design reduces the alignment requirements between the center of the locking hole 111 and the central axis of the guide post 231 during assembly, significantly improving the assembly success rate.

[0027] Furthermore, the interior of the connecting part 110 has a cavity 232, one end of the hook 233 is connected to the cavity wall of the cavity 232, and the other end of the hook 233 extends out from the cavity 232.

[0028] The connecting part 110 is internally configured as a cavity 232, with one end of the hook 233 connected to the cavity wall and the other end extending out of the cavity 232. This cavity 232 provides space for the hook 233 to accommodate and move, allowing it to elastically retract or return to its original position during insertion. This ensures smooth entry into the locking hole 111 and reliable engagement and locking with the connecting part 110, preventing jamming or damage due to rigid interference. Optionally, two hooks 233 are used, arranged crosswise and connected at the bottom by a compression spring. In its natural state, the top of the hook 233 extends out of the cavity 232. During insertion into the locking hole 111, the hook 233 is compressed and retracts into the cavity 232, simultaneously compressing the spring. After complete insertion into the locking hole 111, the spring returns to its original position, bringing the hook 233 back to its original position.

[0029] Furthermore, the drone 100 includes a positioning housing 120, which has an opening 121. A connecting portion 110 is connected to the cavity wall of the opening 121, and the opening 121 is used to insert into a first housing 211 or a second housing 221.

[0030] The opening 121 provides precise physical guidance and housing space for the energy device. When the first housing 211 or the second housing 221 is inserted into the opening 121, the inner wall of the opening 121 limits and constrains the top of the housing, ensuring its movement along a predetermined trajectory, thereby guiding the connecting part 110 and the connecting assembly 230 to accurately align and lock. This nested plug-in design integrates load-bearing and positioning functions, enhancing the energy device's resistance to shear and torsion after installation, and preventing wobbling or loosening caused by cantilever connections. Simultaneously, the opening 121 encloses key components such as the connecting part 110 and conductive interfaces, effectively preventing dust and foreign object collisions, and improving the system's reliability in complex outdoor environments. Overall, this structure achieves a unified solution of quick insertion and removal, secure locking, and environmental protection.

[0031] Furthermore, conductive terminals 240 are respectively provided on the top of the first housing 211 and the second housing 221, and a conductive interface (not shown in the figure) is provided inside the opening 121. The conductive terminals 240 are used to connect to the conductive interface.

[0032] This structure utilizes a plug-in connection to establish electrical conductivity between the energy device and the drone 100. When the snap-fit ​​assembly mechanically locks in place, the conductive terminal 240 precisely inserts into the conductive interface, forming a stable and reliable electrical path. This eliminates the need for additional wiring harnesses or manual connections, simplifying the replacement process. This design ensures continuous power transmission and consistent contact pressure, preventing poor contact due to vibration. Optionally, in this embodiment, the conductive terminal 240 is located at the center of the housing, and the conductive interface is located at the center of the opening 121. In other embodiments, the positions of the conductive terminal 240 and the conductive interface can be adjusted according to actual needs.

[0033] Furthermore, the first energy device 210 is a hydrogen fuel cell device, and the second energy device 220 is a power battery device.

[0034] Setting the first energy device 210 as a hydrogen fuel cell device and the second energy device 220 as a power battery device brings significant benefits. First, this configuration allows the UAV 100 to flexibly switch power sources according to mission requirements: for long-endurance, high-payload missions, such as long-distance inspections and long-term monitoring, the hydrogen fuel cell device can be used, leveraging its high energy density and long endurance; while for short-distance, high-frequency missions with frequent takeoffs and landings, such as express delivery and short-range mapping, the power battery device can be used, benefiting from its high charging and discharging efficiency and convenient battery swapping, reducing the cost per use. Second, this complementary configuration effectively alleviates the limitations of a single power source—the pure electric UAV 100 has insufficient endurance, while the hydrogen fuel cell UAV 100 system is costly and has an incomplete hydrogen refueling network. Combining the two allows the same aircraft to meet performance requirements while allowing for the selection of a more economical solution based on budget and scenario. Furthermore, users only need to purchase one UAV 100 and two energy modules to cover various operational needs, significantly reducing equipment investment and idle time, and improving operational economics. In addition to hydrogen fuel cell equipment and power battery equipment, the energy equipment of this UAV 100 system can also be solar cell modules (suitable for high-altitude long-endurance flight, extending endurance through photovoltaic supplementation), supercapacitor modules (for scenarios requiring short-term high-power output, such as rapid climb or heavy-load takeoff), and hydrogen internal combustion engine power generation modules (using a small internal combustion engine fueled by hydrogen to drive a generator for power supply). These different types of energy equipment only need to be configured with a unified housing, snap-fit ​​components, and conductive terminals 240 to achieve plug-and-play functionality on the same UAV 100 platform, greatly enhancing the system's mission adaptability and application versatility.

[0035] Furthermore, the top of the first housing 211 is provided with a first groove 211a, and the guide post 231 on the first housing 211 is disposed inside the first groove 211a; the top of the second housing 221 is provided with a second groove 221a, and the guide post 231 on the second housing 221 is disposed inside the second groove 221a.

[0036] The groove provides physical protection and spatial constraint for the guide post 231, preventing damage or deformation due to impacts, transportation, or misoperation when the guide post 231 is not in the plugged-in state, thus ensuring that the guiding accuracy is not affected during plugging-in. Simultaneously, the sidewall of the groove acts as an auxiliary guide during plugging-in, guiding the top of the housing smoothly into the opening 121 at the bottom of the UAV 100, pre-aligning the guide post 231 with the locking hole 111, reducing the requirements for operational precision. Furthermore, the groove embeds the guide post 231 below the housing surface, making the top of the housing flat, facilitating stacking and storage, and reducing the risk of snagging on external components. This design improves the durability of the energy module and the convenience of daily use while ensuring connection reliability.

[0037] Furthermore, the hybrid unmanned aerial vehicle system also includes a transport device 300, which includes a roller 310, a base 320, a lifting assembly 330, and a support platform 340. The roller 310 is connected to the bottom of the base 320, and the support platform 340 is connected to the base 320 through the lifting assembly 330. The support platform 340 is used to place the first energy device 210 or the second energy device 220.

[0038] Understandably, the base 320 supports the overall structure, and the casters 310 are mounted on the bottom of the base 320 for flexible movement, facilitating the transfer of energy equipment to the drone 100 or a designated location at the battery swapping station from the ground or in a hangar. The support platform 340 holds the energy equipment and is connected to the base 320 via a lifting assembly 330. It can lift the energy equipment to a suitable docking height based on the drone 100's docking height or the location of the swapping interface, ensuring accurate alignment and locking of the guide post 231, snap-fit ​​assembly, and conductive terminal 240 on the top of the housing with the connection part 110, opening 121, and conductive interface on the bottom of the drone 100. Furthermore, the transport equipment 300 can be standardized, compatible with both the first housing 211 and the second housing 221, allowing for stable placement and transport of both power battery equipment and hydrogen fuel cell equipment, thereby further reducing operating costs and improving overall system availability. Optionally, the transport equipment 300 can be a manual trolley, an electric trolley, or an AGV (Automated Guided Vehicle). Manual trolleys require no batteries, motors, or control systems, resulting in the lowest cost and minimal maintenance. Because they are independent of electricity and programming, they can be used during power outages or in adverse road conditions. Electric trolleys offer a degree of automation, can carry heavier loads, significantly reduce labor intensity, and are easy to operate, requiring no complex programming or system integration; workers can use them after short-term training. AGVs require no manual driving and can operate continuously along preset routes, saving labor costs. They are equipped with built-in lidar, safety edges, and audible and visual alarms, automatically slowing down or stopping when encountering obstacles, making them more suitable for complex environments with mixed human and machine traffic and ideal for automated production lines. The type of transport equipment 300 can be selected based on actual needs and is not specifically limited here.

[0039] Furthermore, the lifting assembly 330 includes a telescopic bracket 130 and a drive component. The bottom of the telescopic bracket 130 is connected to the base 320, and the top of the telescopic bracket 130 is connected to the support platform 340. The drive component is disposed inside the telescopic bracket 130, with the fixed end of the drive component connected to the base 320 and the output end of the drive component connected to the support platform 340.

[0040] The lifting assembly 330, through the cooperation of the telescopic bracket 130 and the drive component, enables the smooth lifting and lowering of the support platform 340. The telescopic bracket 130 connects to the base 320 at its bottom and to the support platform 340 at its top, providing multi-level guidance and anti-torsional support for the platform, ensuring the stability of the energy equipment's posture during lifting and preventing swaying that could lead to docking deviations. The drive component is housed inside the telescopic bracket 130, with its fixed end connected to the base 320 and its output end connected to the support platform 340. This concealed layout not only saves external space, making the transport equipment 300 more compact, but also utilizes the telescopic bracket 130 as a protective cover for the drive component, preventing dust, foreign objects from entering, or accidental contact by personnel, thus improving safety and environmental adaptability. During operation, the drive component extends, pushing the support platform 340 to a predetermined height; when retracted, the platform lowers, facilitating the placement or removal of the energy equipment. The drive component can be an electric actuator, a lead screw motor, or a hydraulic cylinder, etc.

[0041] Furthermore, a first positioning part 341 is provided on the support platform 340, and a second positioning part is provided on the top of the first housing 211 and the second housing 221 respectively, and the first positioning part 341 and the second positioning part are positioned and inserted together.

[0042] By using positioning and plugging to constrain the position of the energy device on the support platform 340, it ensures that the housing is in a unique and repeatable fixed posture relative to the transport equipment 300 each time it is placed. This provides a consistent spatial reference for subsequent lifting and docking, preventing the guide column 231 and snap-fit ​​components from failing to accurately align with the bottom interface of the UAV 100 due to manual placement deviations. Simultaneously, positioning and plugging prevents the energy device from slipping or tipping over during transport, improving transport safety. Optionally, the first positioning part 341 can be a block-shaped structure, column-shaped structure, or conical structure protruding from the support platform 340, and the second positioning part can be a groove-shaped or hole-shaped structure. Of course, in some embodiments, the first positioning part 341 can also be a groove-shaped or hole-shaped structure, and the second positioning part can be a protruding block-shaped structure, column-shaped structure, or conical structure.

[0043] Further, see Figure 6 and Figure 7 In this embodiment, the first energy device is a hydrogen fuel cell device. The hydrogen fuel cell power supply system is a highly integrated modular energy device, the core of which lies in the efficient conversion of the chemical energy of hydrogen into electrical energy through the coordinated work of various assemblies and components. The hydrogen fuel cell power supply system mainly includes a hydrogen fuel reactor system 216, a hydrogen storage system 213, a high-voltage battery system, a frame system 217, a circuit connector 215, a muffler assembly 218, and a thermal management system 214, etc.

[0044] The hydrogen fuel cell reactor system 216 is the "power generation heart" of the entire system. It consists of a stack of multiple individual cells connected in series. Each cell contains a proton exchange membrane, a catalyst layer, and bipolar plates. Its working principle is based on an electrochemical reaction: hydrogen gas dissociates into hydrogen ions and electrons in the anode catalyst layer. Electrons output current through an external circuit, while hydrogen ions pass through the proton exchange membrane to the cathode, where they combine with oxygen and electrons to form water. The reactor's operation relies on the precise coordination of the gas supply system, the hydrogen storage system 213, and the controller. The gas (hydrogen and oxygen) supply system is responsible for regulating the gas inlet conditions of the reactor: on the hydrogen side, an ejector pump or hydrogen circulation pump is typically used to depressurize the high-pressure hydrogen released from the hydrogen storage system 213 and send it into the anode channel, while simultaneously recovering unreacted hydrogen to improve utilization; on the oxygen side (or air side), filtered air is sent into the cathode channel through an air filter, compressor, or blower to provide the oxidant required for the reaction.

[0045] The hydrogen storage system 213 generally adopts a high-pressure gaseous hydrogen storage scheme, which consists of a hydrogen storage cylinder made of carbon fiber wound composite material, cylinder valve, pressure reducing valve and pressure sensor. Its function is to store hydrogen in a high-density, low-mass manner and stabilize the outlet pressure to the value required by the reactor through two-stage pressure reduction.

[0046] The high-voltage battery system acts as a buffer and starting power source within the system. It consists of a lithium-ion battery pack and a battery management system. Its main functions include: supplying power to components such as the gas compressor, controller, and thermal management system 214 during the initial startup phase; operating in parallel with the stack output when the reactor power ramps up slowly to meet the peak power requirements of the UAV 100; and maintaining the controller and cooling fan's brief operation in the event of a sudden stack shutdown or failure. The gas supply controller and the hydrogen fuel cell controller together form the system's control brain. The former collects signals such as hydrogen supply pipeline pressure, air flow, and ambient temperature to drive the start, stop, and speed adjustment of various solenoid valves, pumps, and compressors; the latter monitors the reactor's voltage, current, temperature, and impedance in real time, executes hydrothermal management strategies, and communicates with the UAV 100 flight control system and the high-voltage battery management system via a CAN bus.

[0047] The frame system 217 provides structural support and positioning reference for all components. It typically uses a vibration-damping frame made of high-strength aluminum alloy or carbon fiber composite material, with internal shock-absorbing pads and limiting grooves to ensure that each system maintains its relative position during battery swapping and flight vibrations.

[0048] The circuit connector 215 consists of two parts: a high-voltage high-current circuit and a low-voltage signal circuit. The high-voltage circuit combines the outputs of the reactor and the high-voltage battery and connects them to the power bus of the UAV 100 through high-power terminals that are protected against reverse connection and short circuit. The low-voltage circuit transmits control signals, status feedback and auxiliary power, realizing "plug and play" electrical identification and handshake protocol.

[0049] The silencer assembly 218 is mainly used to suppress the intense noise generated by high-speed airflow in gas supply systems, especially in centrifugal compressors or Roots blowers in oxygen (air) supply subsystems, and hydrogen circulation pumps. The airflow pulsations at the inlet and outlet, and the pressure changes during valve opening and closing, all generate broadband aerodynamic noise during high-speed operation. Silencers typically employ a reactive-resistive composite structure: the reactive part uses an expansion chamber or side-branch resonant cavity with abrupt cross-section changes to cause sound waves of specific frequencies to reflect and interfere within the cavity, resulting in opposite phases and mutual cancellation; the resistive part covers the inner wall of the airflow channel with porous sound-absorbing material (such as high-temperature resistant polyimide foam or metal fiber cotton). When sound waves enter the micropores of the material, air vibrations and friction against the pore walls convert sound energy into heat energy, which is then dissipated. In terms of installation and connection, the silencer is connected in series in the pressure-resistant nylon pipeline between the air compressor outlet and the reactor cathode inlet, or in parallel at the bypass valve of the hydrogen circulation pump's return pipeline, to reduce high-frequency sharp noise. To meet the lightweight requirements of the UAV 100, its shell is often made of aluminum alloy thin shell or carbon fiber composite material, and the internal flow channel is optimized with a low-resistance curve to avoid significantly increasing the intake back pressure and affecting the reactor gas supply efficiency. In addition, the silencer assembly 218 also integrates an anti-icing vent valve or condensate drain hole to prevent ice crystals from clogging the pipeline due to a sudden drop in pressure in low-temperature and high-humidity environments. With the coordination of the gas supply controller, the system can adjust the compressor speed in real time according to the stack power, and the silencer will always keep the exhaust noise within the airworthiness range of the UAV 100 and the range that the operator's ears can tolerate under different flow conditions. Ultimately, the muffler's role in the entire hydrogen fuel cell power supply system is to ensure that, during high-power operations such as hovering and climbing, the gas source noise of the UAV 100 does not interfere with onboard acoustic sensors (such as microphone arrays and flaw detectors) or violate urban low-altitude flight noise restrictions, while simultaneously improving operator comfort. Optionally, this assembly is connected to the frame system 217 via a rubber shock-absorbing bracket 130 to prevent compressor vibration from being rigidly transmitted to the UAV 100 fuselage through the muffler. It also works in conjunction with the shielded signal line in the circuit connector 215, reserving an interface through the active noise reduction algorithm in the controller to achieve further noise suppression. In battery swapping mode, the muffler is replaced along with the entire gas supply module via a locking system. Its interface uses quick-release clamps or V-groove flanges to ensure sealing and low pressure loss even after multiple insertions and removals.

[0050] The thermal management system 214 is used to remove the heat generated by the electrochemical reaction in the reactor (efficiency of about 40%~60%, the rest is dissipated as heat). It generally adopts liquid cooling: the coolant flows through the cooling channel in the reactor bipolar plate and enters the heat sink with a fan. The fan speed and circulation pump flow are adjusted by the temperature control strategy to keep the stack operating temperature stable in a suitable range of 60~80℃.

[0051] The various systems are interconnected via rigid piping, flexible hoses, high-voltage wiring harnesses, shielded communication cables, and mechanical fasteners: the hydrogen storage tank outlet is connected to a pressure reducing valve via a stainless steel high-pressure pipeline, and then to the hydrogen supply module via a low-pressure hose; the air filter is connected to a centrifugal compressor, and then to the cathode inlet via a pressure-resistant nylon tube; the cooling pipeline uses silicone tubing with quick-connect fittings to connect the fuel cell stack, water pump, and radiator in series; the high- and low-voltage wiring harnesses are led out from the reactor current collector and the high-voltage battery terminal, respectively, and converge at circuit connector 215 after passing through a contactor and a fuse. Ultimately, the entire hydrogen fuel cell power supply system, through a unified mechanical and electrical interface and under the action of the battery swapping locking mechanism, can function as an energy module completely interchangeable with the power battery, enabling the UAV 100 to quickly switch to hydrogen-electric mode when performing long-endurance missions, significantly improving its range.

[0052] The above description is merely a preferred 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 hybrid unmanned aerial vehicle (UAV) system, characterized in that, include: A drone (100) having a connecting part (110) at its bottom. A first energy device (210) includes a first housing (211). The second energy device (220) includes a second housing (221); The top of the first housing (211) and the second housing (221) are respectively provided with connecting components (230), which are used to engage with the connecting part (110).

2. The hybrid unmanned aerial vehicle system according to claim 1, characterized in that, The connecting part (110) is provided with a locking hole (111). The connecting component (230) includes a guide post (231) and a hook (233). The hook (233) is connected to the guide post (231). When the guide post (231) and the hook (233) are inserted into the locking hole (111), the hook (233) abuts against the connecting part (110).

3. The hybrid unmanned aerial vehicle system according to claim 2, characterized in that, The connecting part (110) has a cavity (232) inside, one end of the hook (233) is connected to the cavity wall of the cavity (232), and the other end of the hook (233) extends out from the cavity (232).

4. The hybrid unmanned aerial vehicle system according to claim 1, characterized in that, The drone (100) includes a positioning shell (120) having an opening (121), and a connecting part (110) connected to the cavity wall of the opening (121). The opening (121) is used to insert into the first shell (211) or the second shell (221).

5. The hybrid unmanned aerial vehicle system according to claim 4, characterized in that, The top of the first housing (211) and the second housing (221) are respectively provided with conductive terminals (240), and the inside of the opening (121) is provided with a conductive interface. The conductive terminals (240) are used to be plugged into the conductive interface.

6. The hybrid unmanned aerial vehicle system according to claim 1, characterized in that, The first energy device (210) is a hydrogen fuel cell device, and the second energy device (220) is a power battery device.

7. The hybrid unmanned aerial vehicle system according to claim 1, characterized in that, The top of the first housing (211) is provided with a first groove (211a), and the guide post (231) on the first housing (211) is disposed inside the first groove (211a); the top of the second housing (221) is provided with a second groove (221a), and the guide post (231) on the second housing (221) is disposed inside the second groove (221a).

8. The hybrid unmanned aerial vehicle system according to any one of claims 1-7, characterized in that, The hybrid unmanned aerial vehicle system also includes a transport device (300), which includes a roller (310), a base (320), a lifting assembly (330), and a support platform (340). The roller (310) is connected to the bottom of the base (320), and the support platform (340) is connected to the base (320) through the lifting assembly (330). The support platform (340) is used to place the first energy device (210) or the second energy device (220).

9. The hybrid unmanned aerial vehicle system according to claim 8, characterized in that, The lifting assembly (330) includes a telescopic bracket (130) and a drive component. The bottom of the telescopic bracket (130) is connected to the base (320), and the top of the telescopic bracket (130) is connected to the support platform (340). The drive component is disposed inside the telescopic bracket (130), with the fixed end of the drive component connected to the base (320) and the output end of the drive component connected to the support platform (340).

10. The hybrid unmanned aerial vehicle system according to claim 8, characterized in that, The support platform (340) is provided with a first positioning part (341), and the top of the first housing (211) and the second housing (221) are respectively provided with a second positioning part, and the first positioning part (341) and the second positioning part are positioned and inserted together.

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