Retractable drone fuselage based on a hydrogen-electric hybrid power supply dual-layer stacked structure

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a retractable UAV fuselage based on a double-layer stacked structure powered by a hydrogen-electric hybrid system. The fuselage body has folding arm structures on both sides, each including a base fixed to the fuselage, a first arm hinged to the base, and a second arm hinged to the first arm. The second arm has a drive motor and rotor at its end. The outer side of the first arm has a slot for accommodating the second arm in the folded state. The base has a first locking component at its end, and a second locking component is located at the hinge point between the first and second arms. This invention achieves a compact fuselage by using a two-stage folding configuration combined with slot storage and an embedded design of storage and clearance slots, a stacked hydrogen power system, front-end integration of the avionics module, and rear-end arrangement of the hydrogen power system. Corrugated conduits guide the cables to reduce bending damage.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a retractable UAV fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure. Background Technology

[0002] With the popularization of consumer-grade aerial photography, industry-grade power line inspection, agricultural plant protection, geographic surveying and mapping, emergency search and rescue, last-mile logistics and other scenarios, the requirements for drones in terms of portability, transport friendliness and deployment / storage efficiency continue to increase: personal users need the equipment to fit into an everyday backpack, industry users need to place it in the trunk of a car / rescue kit, and logistics drones need to compress the single unit volume to improve stacking and transfer efficiency. Therefore, the folding arm structure has become the core standard feature of portable drones. Currently, the deployed wheelbase of mainstream quadcopter drones is usually quite large. If non-foldable arms are used, the folded length is almost equal to the wheelbase, making it unsuitable for typical portable applications. Even existing foldable solutions generally suffer from common shortcomings: First, most existing foldable drones use single-stage hinge folding, where the arms can only be folded once "against the body". The folded length is equal to the full length of a single arm segment, and the end-drive motor and rotor protrude from the body outline, making them susceptible to damage during transportation. The rotors also need to be disassembled for storage, which is cumbersome for users. A few two-stage folding solutions only fold the arms in half, leaving the second-stage arms / motors exposed. The overall thickness after folding is large, making them unsuitable for compact storage scenarios such as backpacks and trunks. Secondly, most existing two-stage folding drones have "two-section hinged folding" arms. After folding, the second arm is still outside the first arm and has no embedded storage design. This results in a large overall width and thickness after folding. In addition, the motor at the end of the second arm has no dedicated space to make way for it. It either protrudes from the body or needs to be disassembled, making it difficult to store. Third, the cables (motor power lines and signal lines) inside the arms of traditional drones are mostly directly run through the arm cavity. When folded, the cables are repeatedly bent at the hinge. Without a protective structure, the bending life of ordinary cables is limited. After frequent folding and use of portable drones, internal cable breakage is likely to occur, causing malfunctions such as motor loss of control and loss of flight control signals. In addition, in traditional hydrogen-powered drones, hydrogen cylinders are mostly installed on the outside or inside of the fuselage using independent brackets, which takes up a lot of space and increases the structural weight. The components of the hydrogen power system are mostly laid out in a flat manner, which occupies a large area laterally and is not conducive to miniaturization of the overall size. In view of this, the present invention proposes a retractable drone fuselage based on a double-layer stacked structure with hydrogen-electric hybrid power supply. Summary of the Invention

[0003] This invention proposes a retractable drone fuselage based on a double-layer stacked structure of hydrogen-electric hybrid power supply, which solves the technical problems of exposed arms / motors and insufficient reliability of locking when the existing retractable hydrogen fuel cell drones are folded and stored, as well as the difficulty in balancing the layout of the hydrogen power system with the miniaturization of the whole machine.

[0004] The technical solution of the present invention is as follows: a retractable drone fuselage based on a hydrogen-electric hybrid power supply double-layer stacked structure, including a main body, with folding arm structures on both sides of the main body. The folding arm structures are used to fold to reduce the overall size of the main body. The folding arm structures include a base fixedly connected to the outer wall of the main body. A first arm is hinged to the inner side of the base, and a second arm is hinged to the outer end of the first arm. A drive motor and a rotor are fixedly connected to the end of the second arm. A slot is provided on the outer side of the first arm to fold and store the second arm. A storage groove is provided on the outer wall of the main body to accommodate the folded first arm. A clearance groove is provided at the end of the storage groove to accommodate the folded drive motor. A first locking component is provided at the end of the base to lock the unfolded first arm, and a second locking component is provided at the hinge point between the first arm and the second arm to lock the unfolded second arm.

[0005] In the above solution, the first arm can rotate around the hinge axis of the base to achieve a first-stage folding, and the second arm can rotate around the hinge axis at the end of the first arm to achieve a second-stage folding. After folding, the second arm can be embedded in the slot on the outside of the first arm for storage, effectively shortening the storage length. The first locking component and the second locking component can be locked after the two-stage arms are unfolded to ensure the connection rigidity and structural stability of the arms in the unfolded state. Through the configuration of two-stage folding and embedded storage, the overall storage size is compressed, making it suitable for compact storage scenarios.

[0006] By setting a storage slot on the outer wall of the main body that matches the thickness of the first arm, and opening a clearance slot at the end of the storage slot that conforms to the outline of the drive motor, the first arm can be embedded into the body after folding, with its outer surface nearly flush with the body. At the same time, the drive motor and rotor can fall into the dedicated clearance space, realizing the embedded storage of the arm and power system. This not only reduces the overall thickness and volume of the drone after folding, but also effectively avoids damage to the rotor or motor due to collisions during transportation.

[0007] Preferably, the first locking component includes a first extension plate fixedly connected to the end of the base, a first positioning member is provided on the first extension plate, a first guide groove is provided at the end of the first arm that is clearance-fitted with the end of the first positioning member, and a first positioning hole is provided at the end of the first guide groove that is slidably fitted with the end of the first positioning member.

[0008] In the above scheme, by setting a first positioning element on the first extension plate and correspondingly opening a first guide groove and a first positioning hole at the end of the first arm, when the first arm rotates and unfolds, the first positioning element can first slide along the first guide groove for pre-positioning and centering. After the first arm unfolds, the first positioning element automatically falls into the first positioning hole to form a rigid lock. The cooperation between the guide groove and the positioning hole provides fault tolerance for the locking process. Even if there is a slight deviation between the first positioning element and the positioning hole, it can be automatically corrected, ensuring the success rate and convenience of unfolding and locking.

[0009] Preferably, the first positioning member includes a first guide seat fixedly connected to the top of the first extension plate, a first positioning rod slidably connected to the first guide seat and passing through the first guide seat and the first extension plate, the bottom end of the first positioning rod slidingly engaging with the first positioning hole, and a first pull block fixedly connected to the top end of the first positioning rod.

[0010] In the above solution, through the sliding cooperation of the first pull block, the first positioning rod and the first guide seat, the operator only needs to pull the first pull block to drive the positioning rod out of the positioning hole. After being released, the positioning rod automatically falls into the positioning hole by gravity or elastic reset component to lock. The unfolding and folding operations do not require additional tools, realizing quick disassembly and assembly and single-step locking, effectively improving the efficiency of on-site deployment and withdrawal of UAVs.

[0011] Preferably, a first stop is slidably connected to the inner side of the first guide seat, and a first spring is sleeved on the inner side of the first guide seat, with the two ends of the first spring abutting against the inner wall of the first guide seat and the first stop, respectively.

[0012] In the above scheme, by setting a first spring and a first stop inside the first guide seat, the elastic force of the first spring continuously pushes the first positioning rod downward, so that the first positioning rod always maintains a stable locking force after entering the first positioning hole, avoiding the positioning rod from loosening due to flight vibration; at the same time, the first stop provides a stable guide for the first spring, preventing the spring from twisting or jamming during frequent extension and retraction, ensuring the reliability and durability of the locking structure in high-frequency folding use.

[0013] Preferably, the second locking component includes a second extension plate fixedly connected to the end of the first arm, a second positioning member is provided on the second extension plate, a second guide groove is provided on the top wall of the second arm that is clearance-fitted with the end of the second positioning member, and a second positioning hole is provided at the end of the second guide groove that is slidably fitted with the end of the second positioning member.

[0014] In the above scheme, the second locking component is set independently of the first locking component, realizing independent locking and unlocking of the two-stage arms. When unfolding, the first arm is locked first and then the second arm is locked. When folding, the operation is reversed, and the process is clear and there is no cross interference. The cooperation between the second guide groove and the second positioning hole enables the second arm to automatically complete pre-positioning and precise locking during the unfolding process, ensuring that the second arm can withstand the bending moment in the vertical direction after unfolding. This effectively suppresses the damage to the hinge point caused by the gyroscopic effect generated by the high-speed rotation of the rotor, and enhances the rigidity of the arm end and the flight stability.

[0015] Preferably, the second positioning member includes a second guide seat fixedly connected to the top of the second extension plate, a second positioning rod slidably connected to the second guide seat and passing through the second guide seat and the second extension plate, the bottom end of the second positioning rod slidingly engaging with the second positioning hole, and a second pull block fixedly connected to the top of the second positioning rod.

[0016] In the above scheme, the cooperation method between the second positioning rod and the second pull block is consistent with that of the first locking component, which allows the operator to quickly lock and unlock the two-stage arms, reducing the complexity of operation and the probability of misoperation, and further improving the efficiency of rapid on-site deployment of UAVs.

[0017] Preferably, a second stop is slidably connected to the inner side of the second guide seat, and a second spring is sleeved on the inner side of the second guide seat. The two ends of the second spring abut against the inner wall of the second guide seat and the inner wall of the second stop, respectively.

[0018] In the above scheme, the second spring provides a continuous downward locking force to the second positioning rod, ensuring that the second arm always maintains a reliable locked state during flight; the second stop effectively limits and guides the second spring, preventing it from becoming unstable during frequent extension and retraction, ensuring the stability of the second locking component, and improving the structural safety of the UAV under complex flight attitudes.

[0019] Preferably, a first corrugated pipe for guiding cables is fixedly connected between the first arm and the main body, and a second corrugated pipe for guiding cables is fixedly connected between the first arm and the second arm.

[0020] In the above solution, a first corrugated pipe and a second corrugated pipe are respectively set at the two hinge points between the first arm and the body and between the first arm and the second arm as cable channels. The corrugated pipe can flexibly bend and deform with the rotation of the arm, avoiding the problem of repeated sharp-angle bending at the hinge point when the cable passes through the cavity of the traditional arm.

[0021] Preferably, a hydrogen cylinder is installed at the rear end of the main body; a stacked hydrogen power system is provided at the rear end of the main body, and the stacked hydrogen power structure is used to compress the lateral volume occupied by the retractable drone body to adapt to the embedded storage of the folding arm structure.

[0022] In the above solution, the overall outline is reduced while ensuring structural strength by placing the hydrogen cylinder at the rear of the main body; the hydrogen power system adopts a vertically stacked integrated layout, which reduces the horizontal area occupied compared with the traditional flat layout, and is conducive to compressing the overall storage volume of the machine.

[0023] The beneficial effects of this invention are as follows: 1. Through a two-stage folding configuration where the base is hinged to the first arm and the first arm is hinged to the second arm, the first arm is embedded in the storage slot after folding. This allows the second arm to be rotated and folded before being pushed into the slot for concealment when folding, unlike the traditional two-stage folding configuration where the second arm is still attached to the outside of the first arm. Furthermore, the outer wall of the fuselage body has a storage slot that matches the thickness of the first arm, and the end of the storage slot has a clearance slot that conforms to the outline of the drive motor. After the first arm is folded, its outer surface is flush with the fuselage body, and the drive motor and rotor fall into the clearance slot, achieving embedded storage of the arm and power system. This design solves the problem that traditional single-stage folding cannot meet the folding requirements of compact scenarios.

[0024] 2. A first corrugated pipe and a second corrugated pipe are respectively installed at the two hinge points between the first arm and the body, and between the second arm and the first arm, as cable channels. The corrugated pipe undergoes flexible deformation as the arm rotates, forcing the internal motor power lines and signal lines to bend at a preset large curvature radius, solving the problem of repeated sharp-angle bends at the hinge points when the cable passes through the cavity of the traditional arm.

[0025] 3. The second arm adopts a compound action of first sliding out along the slot and then rotating around the hinge axis to unfold. The slot serves as both a hidden storage position in the folded state and a sliding guide position before unfolding, making it a dual-purpose slot. The two-level locking is separate and independent. When unfolding, the first arm is locked first, and then the second arm is unfolded and locked. When folding, the operation is reversed. The process is clear and there is no cross interference. Single-person operation of multiple arms takes less time and is suitable for the efficiency needs of industry users (power inspection, plant protection, search and rescue) for rapid deployment / withdrawal on site.

[0026] 4. Compared to the structure of traditional hydrogen-powered drones where hydrogen cylinders are installed separately and require heavy-duty supports, placing the hydrogen cylinders at the rear of the main body of the drone ensures structural strength while reducing the size of the drone body; the composite gas cylinder valve is located externally at the rear of the main body of the drone body, allowing for hydrogen cylinder replacement, hydrogen filling, and on / off operations without disassembling the drone body; the hydrogen power system adopts a vertically stacked integrated layout, which reduces the lateral area occupied compared to the traditional flat layout, thus compressing the overall storage volume of the drone. Attached Figure Description

[0027] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0028] Figure 1 This is a schematic diagram of the structure of the arm of the present invention in the deployed state; Figure 2 This is a schematic diagram of the structure of the arm in the folded state of the present invention; Figure 3 This is a schematic diagram of the arm folding structure of the present invention; Figure 4 This is a partial structural diagram of the present invention. Figure 1 ; Figure 5 for Figure 4 An enlarged structural diagram at point A in the middle; Figure 6 This is a schematic diagram of the structure of the first positioning element of the present invention; Figure 7 This is a partial structural diagram of the present invention. Figure 2 ; Figure 8 for Figure 7 A magnified structural diagram at point B; Figure 9 This is a schematic diagram of the structure of the second positioning element of the present invention.

[0029] In the diagram: 1. Main fuselage; 2. Folding arm structure; 20. Rotor; 21. Base; 22. First arm; 23. Second arm; 24. Drive motor; 25. Slot; 26. First bellows; 27. First locking assembly; 271. First extension plate; 272. First positioning element; 2721. First guide seat; 2722. First positioning rod; 2723. First pull block; 2724. First stop block; 2725. First spring; 273. First guide groove; 274. First positioning hole; 28. Second bellows; 29. ​​Second locking assembly; 291. Second extension plate; 292. Second positioning element; 2921. Second guide seat; 2922. Second positioning rod; 2923. Second pull block; 2924. Second stop block; 2925. Second spring; 293. Second guide groove; 294. Second positioning hole; 3. Storage groove; 4. Clearance groove; 5. Hydrogen cylinder; 6. Composite cylinder valve; 7. Hydrogen power auxiliary system; 8. Hydrogen fuel cell stack; 9. Thermal management module; 10. Avionics module. Detailed Implementation

[0030] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0031] like Figures 1 to 9 As shown, this embodiment proposes a retractable drone fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure, including a main body 1. The main body 1 is characterized by having folding arm structures 2 on both sides. These folding arm structures 2 are used to fold the fuselage to reduce its overall size. Each folding arm structure 2 includes a base 21 fixedly connected to the outer wall of the main body 1. A first arm 22 is hinged to the inner side of the base 21, and a second arm 23 is hinged to the outer end of the first arm 22. A drive motor 24 and a rotor 20 are fixedly connected to the end of the second arm 23. A slot 25 is provided on the outer side of the first arm 22 for folding and storage. The second arm 23 has a storage groove 3 on the outer wall of the main body 1 to accommodate the folded first arm 22, and a clearance groove 4 at the end of the storage groove 3 to accommodate the folded drive motor 24; the base 21 has a first locking component 27 at the end to lock the unfolded first arm 22, and a second locking component 29 at the hinge of the first arm 22 and the second arm 23 to lock the unfolded second arm 23; a first corrugated tube 26 for guiding cables is fixedly connected between the first arm 22 and the main body 1, and a second corrugated tube 28 for guiding cables is fixedly connected between the first arm 22 and the second arm 23.

[0032] During deployment, the first arm 22 is first rotated outward around its hinge axis with the base 21 until it is deployed perpendicularly to the fuselage body 1. At this point, the first locking component 27 activates, fixing the end of the first arm 22 relative to the base 21. Subsequently, the second arm 23, which was originally embedded in the slot 25 on the outside of the first arm 22, is pulled out along the slot 25 and then rotated around its hinge axis with the first arm 22 to a horizontally deployed position. The second locking component 29 then activates, locking the relative position of the second arm 23 and the first arm 22. The drive motor 24 and rotor 20 are simultaneously positioned with the second arm 23, and the entire aircraft enters the flight-ready state.

[0033] When folding and storing, first release the second locking component 29, rotate the second arm 23 in the opposite direction and push it into the slot 25 on the outside of the first arm 22 for concealed storage; then release the first locking component 27, causing the first arm 22 (along with the stored second arm 23 and drive motor 24) to rotate in the opposite direction and embed into the storage slot 3 on the outer wall of the main body 1. Since the depth of the storage slot 3 matches the thickness of the first arm 22, the outer surface of the first arm 22 is flush with the outer surface of the main body 1; at the same time, the drive motor 24 slides into the clearance slot 4 at the end of the storage slot 3. The volume of the clearance slot 4 is designed to conform to the outline of the drive motor 24, providing an independent storage space for the drive motor 24 and avoiding interference. The entire folding process can be completed without disassembling the rotor 20.

[0034] During the unfolding and folding process, the first corrugated pipe 26 undergoes flexible deformation as the first arm 22 rotates, providing guidance for the cable passing between the main body 1 and the first arm 22; the second corrugated pipe 28 undergoes flexible deformation as the second arm 23 rotates, providing guidance for the cable passing between the first arm 22 and the second arm 23. The two corrugated pipes effectively prevent fatigue damage to the cable caused by repeated bending.

[0035] This structure, through the cooperation of the first arm 22 with the storage slot 3 and the drive motor 24 with the clearance slot 4, achieves embedded storage of the arms and power system, significantly reducing the overall thickness and volume after folding and eliminating protruding edges. This not only facilitates carrying and transportation but also effectively prevents damage to the rotor 20 or drive motor 24 due to collisions during transport. Simultaneously, the first locking component 27 and the second locking component 29 independently lock the two-stage arms, ensuring the connection rigidity and structural stability of the arms in the unfolded state. The slot 25 design on the first arm 22 allows the second arm 23 to be hidden and stored in the folded state, further optimizing the storage form. Furthermore, the embedded storage design eliminates the need to disassemble the rotor 20, shortening the time required for on-site retrieval and reducing the risk of loss or damage to the rotor 20.

[0036] As a specific embodiment of the present invention, refer to Figure 5 and Figure 6 The first locking component 27 includes a first extension plate 271 fixedly connected to the end of the base 21. A first positioning member 272 is provided on the first extension plate 271. The end of the first arm 22 is provided with a first guide groove 273 that is clearance-fitted with the end of the first positioning member 272. The end of the first guide groove 273 is provided with a first positioning hole 274 that is slidably fitted with the end of the first positioning member 272. The first positioning component 272 includes a first guide seat 2721 fixedly connected to the top of the first extension plate 271. A first positioning rod 2722 is slidably connected to the first guide seat 2721, passing through the first guide seat 2721 and the first extension plate 271. The bottom end of the first positioning rod 2722 is slidably engaged with the first positioning hole 274. A first pull block 2723 is fixedly connected to the top end of the first positioning rod 2722. A first stop block 2724 is slidably connected to the inner side of the first guide seat 2721. A first spring 2725 is sleeved on the inner side of the first guide seat 2721. The two ends of the first spring 2725 abut against the inner wall of the first guide seat 2721 and the first stop block 2724, respectively.

[0037] In this embodiment, when the first arm 22 needs to be deployed, the operator pulls the first pull block 2723 upwards, causing the first positioning rod 2722 to compress the first spring 2725 and move upwards. Then, the first arm 22 is rotated outwards to a position perpendicular to the main body 1. After releasing the first pull block 2723, the first positioning rod 2722 returns to its original position downwards under the restoring force of the first spring 2725. During this process, the bottom end of the first positioning rod 2722 first slides along the inclined surface of the first guide groove 273, serving as a pre-positioning and centering mechanism to ensure that the first positioning rod 2722 is accurately aligned with the first positioning hole 274. When the first arm 22 is fully deployed, the first positioning rod 2722 loses support the instant it is directly aligned with the first positioning hole 274 and instantly springs into the first positioning hole 274, forming a rigid connection. The first stop block 2724 moves with the first positioning rod 2722, ensuring that the first spring 2725 is evenly stressed and preventing the positioning rod from jamming. This design utilizes spring potential energy to achieve automatic locking, eliminating the need for additional tightening or levering operations. The deployment action is completed in one step. The inclined design of the first guide groove 273 provides tolerance space, which can automatically correct even if there is a slight deviation between the first positioning rod 2722 and the positioning hole, improving the success rate and convenience of locking. The setting of the first stop 2724 prevents the first spring 2725 from becoming unstable or twisted during high-frequency extension and contraction, ensuring the stability and vibration resistance of the locking structure and ensuring that the arm will not accidentally come loose during flight.

[0038] Compared to locking methods such as threaded locking and lever latching, the spring self-resetting structure of the first locking component 27 requires no additional tools. It can be unlocked by pulling with one hand and automatically locked when released. The operation of unfolding and locking a single first arm 22 is quick, which can improve the overall deployment efficiency of multiple arms.

[0039] As a specific embodiment of the present invention, refer to Figure 8 and Figure 9The second locking component 29 includes a second extension plate 291 fixedly connected to the end of the first arm 22. A second positioning member 292 is provided on the second extension plate 291. A second guide groove 293 is provided on the top wall of the second arm 23, which is in clearance fit with the end of the second positioning member 292. A second positioning hole 294 is provided at the end of the second guide groove 293, which is in sliding fit with the end of the second positioning member 292. The second positioning component 292 includes a second guide seat 2921 fixedly connected to the top of the second extension plate 291. A second positioning rod 2922 is slidably connected to the second guide seat 2921, passing through the second guide seat 2921 and the second extension plate 291. The bottom end of the second positioning rod 2922 is slidably engaged with the second positioning hole 294. A second pull block 2923 is fixedly connected to the top of the second positioning rod 2922. A second stop block 2924 is slidably connected to the inner side of the second guide seat 2921. A second spring 2925 is sleeved on the inner side of the second guide seat 2921. The two ends of the second spring 2925 abut against the inner wall of the second guide seat 2921 and the second stop block 2924, respectively.

[0040] In this embodiment, the deployment of the second arm 23 is based on the locking of the first arm 22. During operation, the second arm 23, hidden in the slot 25 on the outside of the first arm 22, is first pulled out and rotated around the hinge point to unfold. The second positioning rod 2922 maintains a downward trend under the action of the second spring 2925. When the second arm 23 rotates to the horizontal unfolded position, the bottom end of the second positioning rod 2922 slides along the second guide groove 293 and finally falls precisely into the second positioning hole 294. The diameter of the rod body of the second positioning rod 2922 and the inner diameter of the second positioning hole 294 are fitted with a clearance fit, which ensures the firmness of the locking and allows for small assembly tolerances. The second stop 2924 slides in the second guide seat 2921 to provide stable guidance for the second spring 2925. The design combines the sliding storage and rotating deployment of the second arm 23, further shortening the storage length. The second locking component 29 is independent of the first locking component 27, achieving two-level independent locking without interference. This split locking structure improves the stability of the second arm 23's deployment positioning after deployment.

[0041] The slot 25 serves the dual function of a folding storage position and an unfolding sliding guide position. It can realize the extraction and retraction guidance of the second arm 23 without the need for additional guide rails. The slot has two uses, which simplifies the arm structure, reduces the number of parts, and helps to reduce assembly complexity.

[0042] In addition, the first locking component 27 and the second locking component 29 have the same structure and unified operation logic, making them easy for operators to operate; the design of separate independent locking means that the adjustment of one stage of the arm will not affect the locking status of the other stage, making maintenance and debugging more convenient.

[0043] A further preferred embodiment of the present invention is described below. Figure 1 and Figure 2 The rear end of the main body 1 is equipped with a hydrogen cylinder 5. The hydrogen cylinder 5 is compactly installed at the tail and connected to the body through an independent bracket. The hydrogen cylinder 5 is a high-pressure carbon fiber composite cylinder with high-strength structural characteristics. The tail of the hydrogen cylinder 5 faces the tail of the main body 1. The composite cylinder valve 6 at the end of the hydrogen cylinder 5 is externally located at the tail of the main body 1. The composite cylinder valve 6 integrates a switch valve and a filling interface, allowing operators to complete the cylinder opening and closing and hydrogen filling operations directly from outside the machine without disassembling the machine body. At the same time, the hydrogen cylinder 5 can be directly pulled out from the tail for replacement, improving on-site operation efficiency and safety.

[0044] A further preferred embodiment of the present invention is described below. Figure 1 and Figure 2 The rear end of the fuselage body 1 is equipped with a stacked hydrogen power system. The hydrogen power system adopts a vertically stacked functional structure design, including a hydrogen power auxiliary system 7 and a hydrogen fuel cell stack 8. A thermal management module 9 is fixed at the bottom of the fuselage body 1. The front nose of the fuselage body 1 integrates an avionics module 10, which is used to realize flight control, mission payload management and data transmission functions.

[0045] The hydrogen power auxiliary system 7 is fixedly installed in the top space of the hydrogen fuel cell stack 8, integrating functional components such as valve control and status monitoring, enabling rapid response control of the operating status of the hydrogen fuel cell stack 8. The hydrogen fuel cell stack 8 is the core power generation unit, connected to the hydrogen cylinder 5 through a gas supply pipeline, using hydrogen to generate electricity to power the drone. The thermal management module 9 is fixedly installed at the bottom of the fuselage body 1. On the one hand, it regulates the temperature of the hydrogen fuel cell stack 8 and the hydrogen power auxiliary system 7 through a temperature control structure, ensuring that the hydrogen fuel cell stack operates within a suitable temperature range. On the other hand, it optimizes the intake and exhaust channels inside the fuselage, ensuring sufficient intake air flow for the reaction of the hydrogen fuel cell stack 8, so that the hydrogen fuel cell stack can continuously and stably operate in a high-efficiency state, improving power generation efficiency and range.

[0046] Compared to the traditional horizontal tiling scheme, the vertical stacking layout reduces the horizontal area occupied, makes full use of the vertical space at the rear of the main body 1, and makes the outline of the power system more compatible with the storage shape of the fuselage. It does not increase the storage width and works in synergy with the compact design of the arm folding structure 2.

[0047] It is worth noting that this embodiment is also equipped with a conventional energy storage battery and a bidirectional DC / DC converter (both of which can be conventionally installed in the reserved space inside the fuselage). The energy storage battery serves as an auxiliary power source for the initial startup power supply of the hydrogen fuel cell stack, as well as for peak power compensation during instantaneous high-power demand conditions such as takeoff, hovering, or sudden maneuvers. The bidirectional DC / DC converter is electrically connected between the output terminals of the energy storage battery and the hydrogen fuel cell stack, and is used to match the outputs of both to the DC bus to stably drive the drive motor and supply power to the avionics module. During normal cruise, the hydrogen fuel cell stack bears the main power supply load, while the battery provides supplementary power during instantaneous high-power demand, thereby ensuring the continuity and stability of power supply under all operating conditions.

[0048] Overall workflow: I. Deploying Flight Operation Procedures: First, the operator pulls the first lever 2723 of the first locking assembly 27 upwards, causing the first positioning rod 2722 to compress the first spring 2725 and move upwards. Then, the first arm 22 is rotated outwards about its hinge axis with the base 21 until the first arm 22 is extended and perpendicular to the main body 1. Releasing the first lever 2723 causes the first positioning rod 2722 to move downwards under the restoring force of the first spring 2725. Its bottom end first slides along the inclined surface of the first guide groove 273 to pre-position itself, and then precisely slides into the first positioning hole 274, completing the rigid locking of the first arm 22. With the first arm 22 locked, the second arm 23, which was originally embedded in the outer slot 25 of the first arm 22, is pulled out along the slot 25. Then, the second arm 23 is rotated around its hinge axis with the first arm 22 to the horizontally extended position. At this time, the second positioning rod 2922 of the second locking assembly 29 moves down under the action of the second spring 2925, and its bottom end slides along the second guide groove 293 and finally falls into the second positioning hole 294, thus completing the locking of the second arm 23. The drive motor 24 and rotor 20 are positioned with the second arm 23, and the entire aircraft enters the flight preparation state. The composite gas cylinder valve 6 at the tail of the fuselage is opened to supply hydrogen. The high-pressure hydrogen in the hydrogen cylinder 5 is regulated and then delivered to the hydrogen fuel cell stack 8. The hydrogen fuel cell stack 8 generates electricity through electrochemical reaction to power the UAV's power system and avionics system. The thermal management module 9 operates synchronously to regulate the operating temperature of the hydrogen fuel cell stack 8 and ensure the efficient and stable operation of the system.

[0049] The entire deployment process is executed in the order of locking the first arm 22 first, and then unfolding and locking the second arm 23. The actions do not overlap or interfere with each other. A single person can complete the deployment of all four sets of arm folding structures 2. The on-site deployment speed is fast and it is suitable for the rapid take-off operation requirements in scenarios such as power inspection and emergency search and rescue.

[0050] II. Folding and Storage Process: First, the operator pulls the second pull block 2923 upwards to overcome the elastic force of the second spring 2925, causing the second positioning rod 2922 to disengage from the second positioning hole 294, rotating the second arm 23 in the opposite direction to retract it, and pushing it into the slot 25 on the outside of the first arm 22 for concealed storage. Pull the first pull block 2723 upwards to disengage the first positioning rod 2722 from the first positioning hole 274. Rotate the first arm 22 (including the retracted second arm 23 and drive motor 24) in the opposite direction around the hinge axis until the first arm 22 is embedded in the storage groove 3 on the outer wall of the main body 1, with its outer surface nearly flush with the body. At the same time, the drive motor 24 at the end of the second arm 23 slides into the clearance groove 4 at the end of the storage groove 3, achieving embedded storage, reducing the overall size of the machine, and facilitating storage and transportation. Throughout the unfolding and folding process, the fixedly connected first corrugated pipe 26 undergoes flexible bending deformation as the first arm 22 rotates, providing a continuous and smooth guiding channel for the cable passing through the fuselage body 1 and the first arm 22; the fixedly connected second corrugated pipe 28 undergoes flexible bending deformation as the second arm 23 rotates, providing equal protection for the cable passing through the first arm 22 and the second arm 23. The two corrugated pipes can reduce the risk of sharp-angle bending. After folding, the overall outer surface of the machine is neat and easy to stack and transport in batches; and the flexible protective design of the first corrugated tube 26 and the second corrugated tube 28 can support repeated folding without cable damage.

[0051] When hydrogen needs to be replenished, there is no need to disassemble the outer casing; the filling operation can be carried out directly through the external composite gas cylinder valve 6 at the rear of the machine. When replacing the gas cylinder, the hydrogen cylinder 5 can be directly pulled out from the rear of the machine for replacement, making the operation convenient and safe.

[0052] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as defined by the appended claims and their equivalents.

Claims

1. A retractable unmanned aerial vehicle (UAV) fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure, comprising a fuselage body (1), characterized in that, The fuselage body (1) is equipped with arm folding structures (2) on both sides. The arm folding structures (2) are used to fold the fuselage body (1) to reduce its overall size. The arm folding structures (2) include a base (21) fixedly connected to the outer wall of the fuselage body (1). A first arm (22) is hinged to the inner side of the base (21). A second arm (23) is hinged to the outer end of the first arm (22). A drive motor (24) and a rotor (20) are fixedly connected to the end of the second arm (23). The outer side of the first arm (22) is... A slot (25) is provided on the side to fold and store the second arm (23). A storage groove (3) is provided on the outer wall of the main body (1) to accommodate the folded first arm (22). A clearance groove (4) is provided at the end of the storage groove (3) to accommodate the folded drive motor (24). A first locking component (27) is provided at the end of the base (21) to lock the unfolded first arm (22). A second locking component (29) is provided at the hinge of the first arm (22) and the second arm (23) to lock the unfolded second arm (23).

2. The retractable drone fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure according to claim 1, characterized in that, The first locking component (27) includes a first extension plate (271) fixedly connected to the end of the base (21). The first extension plate (271) is provided with a first positioning member (272). The end of the first arm (22) is provided with a first guide groove (273) that is clearance-fitted with the end of the first positioning member (272). The end of the first guide groove (273) is provided with a first positioning hole (274) that is slidably fitted with the end of the first positioning member (272).

3. The retractable drone fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure according to claim 2, characterized in that, The first positioning member (272) includes a first guide seat (2721) fixedly connected to the top of the first extension plate (271), a first positioning rod (2722) slidably connected to the first guide seat (2721) and the first extension plate (271), the bottom end of the first positioning rod (2722) slidably engaging with the first positioning hole (274), and the top end of the first positioning rod (2722) fixedly connected to a first pull block (2723).

4. The retractable drone fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure according to claim 3, characterized in that, The first guide seat (2721) is slidably connected to the inner side of the first stop (2724), and the first guide seat (2721) is sleeved with the first spring (2725). The two ends of the first spring (2725) abut against the inner wall of the first guide seat (2721) and the first stop (2724), respectively.

5. The retractable drone fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure according to claim 1, characterized in that, The second locking assembly (29) includes a second extension plate (291) fixedly connected to the end of the first arm (22), a second positioning member (292) is provided on the second extension plate (291), a second guide groove (293) is provided on the top wall of the second arm (23) and is clearance-fitted with the end of the second positioning member (292), and a second positioning hole (294) is provided at the end of the second guide groove (293) and is slidingly fitted with the end of the second positioning member (292).

6. The retractable unmanned aerial vehicle fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure according to claim 5, characterized in that, The second positioning member (292) includes a second guide seat (2921) fixedly connected to the top of the second extension plate (291), a second positioning rod (2922) slidably connected to the second guide seat (2921) and the second extension plate (291), the bottom end of the second positioning rod (2922) slidably engaging with the second positioning hole (294), and a second pull block (2923) fixedly connected to the top of the second positioning rod (2922).

7. The retractable drone fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure according to claim 6, characterized in that, The second guide seat (2921) is slidably connected to the inner side of the second stop (2924), and the second guide seat (2921) is sleeved with the second spring (2925). The two ends of the second spring (2925) abut against the inner wall of the second guide seat (2921) and the inner wall of the second stop (2924), respectively.

8. The retractable unmanned aerial vehicle fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure according to claim 1, characterized in that, A first corrugated tube (26) for guiding cables is fixedly connected between the first arm (22) and the main body (1), and a second corrugated tube (28) for guiding cables is fixedly connected between the first arm (22) and the second arm (23).

9. The retractable unmanned aerial vehicle fuselage based on a hydrogen-electric hybrid power supply with a double-layer stacked structure according to claim 1, characterized in that, The rear end of the fuselage body (1) is equipped with a hydrogen cylinder (5); the rear end of the fuselage body (1) is provided with a stacked hydrogen power system, the stacked hydrogen power structure is used to compress the lateral volume occupied by the retractable drone fuselage to adapt to the embedded storage of the arm folding structure (2).

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