Unmanned aerial vehicle integrated fixing device and hydrogen energy fuel cell

Abstract

The invention relates to the technical field of aircraft fuel cell devices, in particular to an unmanned aerial vehicle integrated fixing device and a hydrogen energy fuel cell. According to the device, through a unique rib structure comprising a plurality of intermittent slots, the top frame, the cover frame and the bottom frame are inserted together in a staggered manner to form a stable integrated structure, so that a first mounting space and a second mounting space which are stable in position and structure are provided for a fuel cell and a hydrogen cylinder; the fuel cell and the hydrogen cylinder which are respectively fixed in the first mounting space and the second mounting space cannot generate relative axial displacement and radial deflection, so that the structural stability and the anti-interference performance of the fuel cell and the hydrogen cylinder on the influence of complex environmental factors are improved; compared with a separated installation design in the prior art, the device does not need to depend on a plurality of fragmentary mechanical fasteners such as bolts, buckles and the like to position the fuel cell and the hydrogen cylinder, and the fixing mode is simple; and the fuel cell and the hydrogen cylinder are simultaneously fastened in the integrated fixing device, so that the space layout is compact, and the structural integrity is higher.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft fuel cell devices, and in particular to an integrated fixing device for unmanned aerial vehicles and a hydrogen fuel cell. Background Art

[0002] At present, the application of UAV equipment in technical fields such as aerial photography, logistics distribution, surveying and mapping, and agricultural plant protection is becoming increasingly in-depth. The endurance and charging capacity of traditional lithium battery-powered UAVs can no longer meet the long-distance and long-term operation requirements in related technical fields. Therefore, hydrogen fuel cells, with their high energy density, long endurance, and environmental protection advantages, have gradually become the research and development direction in the field of UAV energy technology.

[0003] Due to the limitation of technological development, the fuel cells and hydrogen cylinders of existing drones adopt a separate installation design. On the one hand, this design takes up a large space and has a scattered layout, which affects the compactness of the drone structure and leads to a decrease in the flight performance of the drone. On the other hand, this design relies on bolts, buckles and other fragmentary mechanical fasteners to position the fuel cell and hydrogen storage bottle separately. The installation steps are cumbersome and the reliability is insufficient. During the flight of the drone, if the drone vibrates or the attitude changes suddenly due to airflow disturbance or physical impact, the separate design can easily cause relative axial displacement and radial deflection of the fuel cell and hydrogen cylinder, causing the mechanical fasteners to loosen, and causing the hydrogen transmission pipeline to loosen due to repeated stress deformation, affecting the stability of energy supply and posing the risk of airtight failure. The above problems have seriously restricted the practical application of hydrogen-powered drones in long-flight operation scenarios. Summary of the invention

[0004] The present invention aims to provide an integrated fixing device and a hydrogen fuel cell for a drone, so that the fuel cell and the hydrogen cylinder form a stable integrated structure, thereby improving the safety of the drone hydrogen fuel cell and solving the technical problem that the existing separate design easily causes relative axial displacement and radial deflection of the fuel cell and the hydrogen cylinder.

[0005] In order to achieve the above-mentioned object, the first aspect of the present invention provides an integrated fixing device for a drone, comprising a top frame, a cover frame and a bottom frame; the top frame comprises a first support portion extending from its top surface to both sides; the first support portion is provided with a plurality of intermittent slots to form a rib structure; the cross section of the top frame is an inverted U-shape; the cover frame is connected to the first support portion, and the cover frame is provided with a plurality of intermittent slots to form a rib structure; the bottom frame comprises a second support portion extending from its top surface to both sides; the second support portion is provided with a plurality of intermittent slots to form a rib structure; the cross section of the bottom frame is W-shaped; wherein:

[0006] The first supporting part and the second supporting part are staggered and inserted to form a first installation space between the top frame and the bottom frame; the cover frame and the second supporting part are staggered and inserted to form a second installation space between the cover frame and the bottom frame.

[0007] The above-mentioned integrated fixing device for unmanned aerial vehicles uses a unique rib structure including multiple intermittent slots to make the top frame, the cover frame and the bottom frame staggered and plugged together to form a stable integrated structure, thereby providing a first installation space and a second installation space with stable position structure for the fuel cell and the hydrogen cylinder, so that the fuel cell and the hydrogen cylinder respectively fixed in the first installation space and the second installation space cannot produce relative axial displacement and radial deflection, thereby improving its structural stability and anti-interference ability against complex environmental factors; and compared with the separate installation design of the prior art, the device does not need to rely on bolts, snaps and other fragmentary mechanical fasteners to position the fuel cell and the hydrogen cylinder, and the fixing method is simple; the fuel cell and the hydrogen cylinder are fastened in the integrated fixing device at the same time, the spatial layout is compact, the structural integrity is higher, and the protection performance of the fuel cell and the hydrogen cylinder in the face of physical impact is enhanced.

[0008] Preferably, the integrated fixing device for the drone further comprises a first screw and a first nut, a first mounting hole is provided on the top surface of the top frame, and a first screw is fixed on the top surface of the bottom frame; wherein:

[0009] The first screw rod passes through the first mounting hole and is threadedly connected with the first nut to fasten the top frame and the bottom frame.

[0010] This preferred embodiment further uses a first screw to enhance the tightness of the connection between the top frame and the bottom frame, thereby improving the stability of the integrated fixing device; at the same time, the length of the second screw can affect the size of the first installation space formed by the top frame and the bottom frame, and the user can select a second screw of appropriate length for fuel cells of different sizes, thereby making the device more applicable.

[0011] Preferably, the cover frame and the first supporting portion are rotatably connected.

[0012] This preferred embodiment enables the device to rotate and adjust the position of the cover frame according to hydrogen cylinders of different sizes, thereby adjusting the size of the second installation space, making it suitable for hydrogen cylinders of different shapes, thereby improving the scope of application of the device; at the same time, after the hydrogen cylinder is fixed in the second installation space, the position of the cover frame can be rotated to increase the clamping force of the device on the hydrogen cylinder, further preventing the hydrogen cylinder from generating relative axial displacement and radial deflection, thereby enhancing the structural stability of the device and the protection performance of the hydrogen cylinder when facing physical impact.

[0013] Preferably, the above-mentioned integrated drone fixing device further includes a second screw and a second nut; a through chute is formed on the side surface of the cover frame, and a plurality of second mounting holes are formed on the side surface of the second supporting portion; wherein:

[0014] The second screw passes through the through chute and any of the second mounting holes and is threadedly connected to the second nut, so as to fasten the cover frame and the second supporting portion.

[0015] It should be noted that since both the cover frame and the second supporting portion are rib structures, which include a plurality of ribs distributed side by side, and there is an intermittent slot space between every two ribs. Therefore, the through chute formed on the side surface of the cover frame should be understood as: a through chute of the same type is formed on the side surface of each rib in the cover frame, and the plurality of second mounting holes formed on the side surface of the second supporting portion should be understood as: the same plurality of second mounting holes are formed on the side surface of each rib in the second supporting portion. For the convenience of understanding and description, the above structure is briefly described in this application as the through chute formed on the side surface of the cover frame and the plurality of second mounting holes formed on the side surface of the second supporting portion.

[0016] This preferred embodiment cooperates with the cover frame rotating mechanism to form a plurality of second mounting holes on the side surface of the second supporting portion. For hydrogen cylinders of different sizes, when the cover frame is rotated and adjusted to a suitable position, its through chute will align with the second mounting holes at the corresponding positions. At this time, the second screw can pass through the through chute and the corresponding second mounting holes and be threadedly connected to the second nut, realizing the fastening of the cover frame and the second supporting portion, keeping the adjusted size of the second installation space at this moment, and completing the locking and fastening of the hydrogen cylinder in the second installation space.

[0017] Preferably, the above-mentioned integrated drone fixing device further includes a limiting slide bar, which is slidably connected to the through chute, and a pressing block is arranged at the bottom of the limiting slide bar.

[0018] This preferred embodiment cooperates with the cover frame rotating mechanism to slidably connect the limiting slide bar at its through chute. When a hydrogen cylinder is fixed in the second installation space, the limiting slide bar can slide in the through chute in cooperation with the rotation of the cover frame. At this time, the pressing block arranged at the bottom of the limiting slide bar will cooperate with the sliding of the limiting slide bar to press and limit the hydrogen cylinder in the second installation space; when the cover frame rotates to the most suitable position corresponding to the size of this hydrogen cylinder, the limiting slide bar correspondingly slides to the most suitable position corresponding to the size of this hydrogen cylinder, so that the pressing block cooperates to press this hydrogen cylinder and applies sufficient pressure to it, completing the locking and fastening of this hydrogen cylinder.

[0019] Preferably, adjusting blocks are sleeved at both ends of the second screw, and the adjusting blocks press against the through chute.

[0020] This preferred embodiment is combined with a cover frame rotation mechanism and a sliding mechanism of a limiting slide bar. Adjusting blocks are sleeved on both ends of the second screw rod. When the cover frame is rotated and adjusted to a proper position, and the second screw rod passes through the through chute and the corresponding second mounting hole and is threadedly connected to the second nut, the adjusting block pressing against the through chute will press against the limiting slide bar and force it to slide adaptively, so that the limiting slide bar will correspondingly slide to the optimal position corresponding to the size of the hydrogen cylinder, and the pressing block will cooperate to press against the hydrogen cylinder, applying sufficient pressure to it to complete the locking and fastening of the hydrogen cylinder.

[0021] Preferably, a positioning arc hole is formed among the first support portion, the cover frame and the second support portion.

[0022] This preferred embodiment designs a positioning arc hole structure, which facilitates installing the integrated fixing device onto a drone or other equipment through the space of the arc hole. The structure is simple and easy to install and implement.

[0023] Preferably, the above integrated drone fixing device further includes a third screw rod and a third nut, wherein:

[0024] The third screw rod passes through the positioning arc hole and an external drone and is threadedly connected to the third nut, so as to fasten the integrated drone fixing device to the external drone.

[0025] In this preferred embodiment, the third screw rod passes through the arc hole and the external drone, so that the integrated fixing device is fastened to the drone, combined into an integrated drone structure, providing a first installation space and a second installation space with stable position structures for the fuel cell and hydrogen cylinder of the drone. The space layout is compact, the structural integrity is higher, and the protection performance for the fuel cell and hydrogen cylinder against physical impact is enhanced.

[0026] Preferably, the cross section of the cover frame is arc-shaped.

[0027] This preferred embodiment adapts to the cylindrical outer shell of the hydrogen cylinder and designs a cover frame with an arc-shaped cross section, further increasing the fitting area between the cover frame and the hydrogen cylinder, thereby enhancing the clamping force of the cover frame on the hydrogen cylinder fixed in the second installation space, further preventing the hydrogen cylinder from generating relative axial displacement and radial deflection, and enhancing the structural stability of the device and the protection performance for the hydrogen cylinder against physical impact.

[0028] The second aspect of the present invention provides an integrated drone hydrogen energy fuel cell, including the integrated drone fixing device, a fuel cell and a hydrogen cylinder as described in any item of the first aspect of the present invention, wherein:

[0029] The fuel cell is clamped and fixed in the first installation space by the top frame and the bottom frame;

[0030] The hydrogen cylinder is clamped and fixed in the second installation space by the cover frame and the bottom frame;

[0031] The fuel cell is connected to the hydrogen cylinder through an air pipe.

[0032] The above integrated hydrogen energy fuel cell fixes the fuel cell and the hydrogen cylinder in a one-piece fixing device of a drone. Compared with the traditional separated installation design, this design can make the fuel cell and the hydrogen cylinder form an integral structure, and there will be no relative axial displacement and radial deflection between the two, thereby improving the structural stability and anti-interference ability of the hydrogen energy fuel cell against the influence of complex environmental factors, and enhancing its defensive ability against physical impacts. Description of the Drawings

[0033] Figure 1 is a schematic three-dimensional structure diagram of an integrated hydrogen energy fuel cell of a drone provided by an embodiment of the present invention;

[0034] Figure 2 is a schematic rear three-dimensional structure diagram of an integrated hydrogen energy fuel cell of a drone provided by an embodiment of the present invention;

[0035] Figure 3 is a schematic three-dimensional structure diagram of the overall frame of a one-piece fixing device of a drone provided by an embodiment of the present invention;

[0036] Figure 4 is a schematic three-dimensional structure diagram of the bottom frame and the fuel cell of an integrated hydrogen energy fuel cell of a drone provided by an embodiment of the present invention;

[0037] Figure 5 is a schematic three-dimensional structure diagram of the top frame and the cover frame of a one-piece fixing device of a drone provided by an embodiment of the present invention;

[0038] Figure 6 is a schematic three-dimensional structure diagram of the top frame and the cover frame of another one-piece fixing device of a drone provided by an embodiment of the present invention;

[0039] Figure 7 is a schematic bottom three-dimensional structure diagram of the top frame and the cover frame of a one-piece fixing device of a drone provided by an embodiment of the present invention;

[0040] Figure 8 is a schematic three-dimensional structure diagram of the cover frame of a one-piece fixing device of a drone provided by an embodiment of the present invention;

[0041] Figure 9 is a schematic partial three-dimensional structure diagram of a one-piece fixing device of a drone provided by an embodiment of the present invention;

[0042] Figure 10It is an enlarged three-dimensional structural schematic diagram of part A of an integrated fixing device for an unmanned aerial vehicle provided by an embodiment of the present invention;

[0043] Figure 11 It is a partial structural schematic diagram of a limiting mechanism of an integrated fixing device for an unmanned aerial vehicle provided by an embodiment of the present invention;

[0044] Figure 12 It is a partial structural schematic diagram of a limiting mechanism of another integrated fixing device for an unmanned aerial vehicle provided by an embodiment of the present invention;

[0045] Wherein: 1. Bottom frame; 2. Top frame; 3. Fuel cell; 4. Hydrogen cylinder; 5. Intermittent slot; 6. Cover frame; 7. Limiting mechanism; 71. Second mounting hole; 72. Through chute; 73. Limiting slide bar; 74. Connecting block; 75. Pressing block; 76. Second screw; 77. Adjusting block; 78. Second nut; 8. First mounting hole; 9. First screw; 10. First nut; 11. Arc hole; 12. Third screw; 13. Third nut; 14. Air pipe. Detailed implementation manners

[0046] The present invention will be described in detail below with reference to the drawings and in conjunction with embodiments. It should be noted that the following detailed descriptions are all exemplary descriptions, aiming to provide further detailed descriptions of the present invention. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the technical field to which this application belongs; the terms used in the description of this application in the specification are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" and any variations thereof in the specification and claims of this application and the above drawings are intended to cover non-exclusive inclusion. The terms "first", "second", etc. in the specification and claims of this application or the above drawings are used to distinguish different objects and are not used to describe a specific order.

[0047] First, some terms in this application are explained to facilitate understanding by those skilled in the art.

[0048] 1) Unmanned aerial vehicle: Unmanned Aerial Vehicle (UAV) technology is a highly complex system that takes unmanned aerial vehicles as the core and integrates multiple disciplines such as aerodynamics, automatic control, information sensing, and communication navigation.

[0049] 2) Hydrogen energy fuel cell: A hydrogen energy fuel cell (Hydrogen Fuel Cell) is a clean energy device that directly converts the chemical energy of hydrogen into electrical energy through an electrochemical reaction, and its core characteristics are high efficiency and low emission pollution.

[0050] With the wide application of unmanned aerial vehicle (UAV) technology in fields such as aerial photography, logistics distribution, surveying and mapping, and agricultural plant protection, higher requirements have been put forward for its endurance and energy utilization efficiency in related fields. Traditional lithium battery-powered UAVs have problems such as short endurance time and long charging time, making it difficult to meet the requirements of long-distance and long-time operations. Therefore, hydrogen fuel cells, with their advantages of high energy density, long endurance, and environmental protection, have gradually become a research hotspot in the UAV energy field.

[0051] Due to technological development limitations, there are many problems in the structure of the hydrogen fuel cell system of existing UAVs. On the one hand, the current UAV fuel cell and hydrogen cylinder are installed in a separated design, resulting in the fuel cell and hydrogen cylinder occupying too much internal space of the UAV and having a scattered layout, which affects the overall structural compactness and flight performance of the UAV. On the other hand, the existing installation methods often use multiple parts to position the battery and hydrogen cylinder. During use, it is neither convenient to install nor reliable to fix. During the flight of the UAV, due to factors such as vibration and impact, the fuel cell and hydrogen cylinder may be prone to loosening and displacement due to scattered installation, affecting the stability of energy supply and even causing safety problems.

[0052] To solve the above technical problems, referring to Figure 1 and Figure 2 , an embodiment of the present invention provides an integrated hydrogen fuel cell for UAVs, including an integrated fixing device for UAVs, a fuel cell 3, and two hydrogen cylinders 4; the integrated fixing device for UAVs includes a top frame 2, two cover frames 6, and a bottom frame 1.

[0053] Referring to Figure 2 , Figure 3 , Figure 5 , Figure 6 and Figure 7 , the top frame 2 includes a first support portion extending from its top surface to both sides; a number of intermittent slots 5 are provided in the first support portion, thus forming a rib structure; the cross-section of the top frame 2 is in an inverted U shape; the two cover frames 6 are respectively connected to the two sides of the top frame 2 and the first support portion, and a number of intermittent slots 5 are provided in the cover frame 6, thus forming a rib structure.

[0054] Referring to Figures 2 to 4 , the bottom frame 1 includes a second support portion extending from its top surface to both sides; a number of intermittent slots 5 are provided in the second support portion, thus forming a rib structure; the cross-section of the bottom frame 1 is in a w shape.

[0055] Referring to Figures 1 to 3The first supporting part and the second supporting part are staggered and inserted to form a first installation space between the top frame 2 and the bottom frame 1, and the cross-section of the first installation space is rectangular; the cover frame 6 and the second supporting part are staggered and inserted to form a second installation space and a third installation space between the cover frame 6 and the bottom frame 1, and the cross-section of the second installation space and the third installation space is an inverted triangle.

[0056] The fuel cell 3 is clamped and fixed in the first installation space by the top frame 2 and the bottom frame 1;

[0057] The two hydrogen cylinders 4 are clamped and fixed in the second installation space and the third installation space by the cover frame 6 and the bottom frame 1 respectively;

[0058] The fuel cell 3 is connected to the two hydrogen cylinders 4 via a gas pipe 14 .

[0059] The above-mentioned integrated hydrogen fuel cell for unmanned aerial vehicles uses a unique rib structure including multiple intermittent slots 5, so that the top frame 2, the cover frame 6 and the bottom frame 1 are staggered and plugged together to form a stable integrated structure, thereby providing a first installation space and a second installation space with stable position structure for the fuel cell 3 and the hydrogen bottle 4, so that the fuel cell 3 and the hydrogen bottle 4 respectively fixed in the first installation space and the second installation space cannot produce relative axial displacement and radial deflection, thereby improving its structural stability and anti-interference ability against complex environmental factors; and compared with the separate installation design of the prior art, the device does not need to rely on bolts, snaps and other fragmentary mechanical fasteners to position the fuel cell 3 and the hydrogen bottle 4, and the fixing method is simple; the fuel cell 3 and the hydrogen bottle 4 are simultaneously fastened in the integrated fixing device of the unmanned aerial vehicle, with a compact spatial layout and higher structural integrity, thereby enhancing the protection performance of the fuel cell 3 and the hydrogen bottle 4 when facing physical impact.

[0060] Reference Figures 1 to 6 Preferably, the drone integrated fixing device further comprises a first screw 9 and a first nut 10, the top surface of the top frame 2 is provided with two first mounting holes 8, and the top surface of the bottom frame 1 is fixed with two first screws 9 corresponding to the two first mounting holes 8; wherein:

[0061] The first screw rod 9 passes through the corresponding first mounting hole 8 and is threadedly connected with the corresponding first nut 10 to fasten the top frame 2 and the bottom frame 1 .

[0062] This preferred embodiment further uses the first screw 9 to enhance the tightness of the connection between the top frame 2 and the bottom frame 1, thereby improving the stability of the integrated fixing device of the drone. At the same time, the length of the second screw 76 can affect the size of the first installation space formed by the top frame 2 and the bottom frame 1. The user can select a second screw 76 of suitable length for fuel cells 3 of different sizes, thereby making the device more applicable. In addition, the two first screws 9 further confine the fuel cell 3 within the first installation space to prevent the fuel cell 3 from slipping.

[0063] Preferably, the cover frame 6 and the first supporting portion are rotatably connected.

[0064] This preferred embodiment enables the device to rotate and adjust the position of the cover frame 6 according to hydrogen cylinders 4 of different sizes, thereby adjusting the size of the second installation space to make it suitable for hydrogen cylinders 4 of different shapes, thereby improving the applicability of the device; at the same time, after the hydrogen cylinder 4 is fixed in the second installation space, the position of the cover frame 6 can be rotated to increase the clamping force of the device on the hydrogen cylinder 4, further preventing the hydrogen cylinder 4 from generating relative axial displacement and radial deflection, thereby enhancing the structural stability of the device and the protection performance of the hydrogen cylinder 4 when facing physical impact.

[0065] Reference Figures 9 to 10 , Figure 10 : is an enlarged three-dimensional structural diagram of part A of an integrated fixing device for a drone provided by an embodiment of the present invention. Preferably, the integrated fixing device for a drone further comprises a limiting mechanism 7, the limiting mechanism 7 comprises a second screw 76 and a second nut 78; a through-type slide groove 72 is provided on the side of the cover frame 6, and a plurality of second mounting holes 71 are provided on the side of the second support portion; wherein:

[0066] The second screw rod 76 passes through the through-type slide groove 72 and any second mounting hole 71 and is threadedly connected with the second nut 78 to fasten the cover frame 6 and the second supporting portion.

[0067] It should be noted that since the cover frame 6 and the second support part are both rib structures, including a plurality of ribs arranged side by side, there is an intermittent slot 5 between every two ribs. Therefore, the through-type slide groove 72 provided on the side of the cover frame 6 should be understood as: the same through-type slide groove 72 is provided on the side of each rib in the cover frame 6, and the second support part side has a plurality of second mounting holes 71, which should be understood as: the same second mounting holes 71 are provided on the side of each rib in the second support part. For ease of understanding and description, the present application briefly describes the above structure as the through-type slide groove 72 provided on the side of the cover frame 6, and the plurality of second mounting holes 71 provided on the side of the second support part.

[0068] In this preferred embodiment, in cooperation with the rotating mechanism of the cover frame 6, a plurality of second mounting holes 71 are provided on the side surface of the second support portion. For hydrogen cylinders 4 of different sizes, when the cover frame 6 is rotated and adjusted to a suitable position, its through chute 72 will align with the corresponding second mounting hole 71. At this time, the second screw 76 can pass through the through chute 72 and the corresponding second mounting hole 71 and be threadedly connected to the second nut 78, realizing the fastening of the cover frame 6 and the second support portion, keeping the adjusted size of the second installation space at this moment, and completing the locking and fastening of the hydrogen cylinder 4 in the second installation space.

[0069] Refer to Figure 7 , Figure 8 , Figure 11 And Figure 12 , preferably, the limiting mechanism 7 further includes two limiting slide bars 73, and the two limiting slide bars 73 are respectively slidably connected to the through chute 72. The bottom of each limiting slide bar 73 is connected to a pressing block 75 through a connecting block 74.

[0070] In this preferred embodiment, the limiting slide bars 73 are slidably connected to the through chute 72 of the cover frame 6 in cooperation with its rotating mechanism. When a hydrogen cylinder 4 is fixed in the second installation space, the two limiting slide bars 73 can slide in the through chute 72 in cooperation with the rotation of the cover frame 6. At this time, the two pressing blocks 75 provided at the bottoms of the two limiting slide bars 73 will cooperate with the sliding of the limiting slide bars 73 to press and limit the hydrogen cylinder 4 in the second installation space from two directions; when the cover frame 6 is rotated to the most suitable position corresponding to the size of this hydrogen cylinder 4, the limiting slide bars 73 correspondingly slide to the most suitable position corresponding to the size of this hydrogen cylinder 4, so that the two pressing blocks 75 press this hydrogen cylinder 4 from two directions and apply sufficient pressure to it, completing the locking and fastening of this hydrogen cylinder 4.

[0071] In a preferred embodiment, the pressing block 75 is made of rubber material. The rubber material has a relatively high friction coefficient. Selecting rubber material to make the pressing block 75 can increase the pressing friction force of the pressing block 75 on the hydrogen cylinder 4.

[0072] Refer to Figures 9 to 11 , preferably, adjusting blocks 77 are sleeved on both ends of the second screw 76, and the adjusting blocks 77 press against the through chute 72.

[0073] This preferred embodiment cooperates with the rotating mechanism of the cover frame 6 and the sliding mechanism of the limiting slide bar 73. Adjusting blocks 77 are sleeved at both ends of the second screw rod 76. When the cover frame 6 is rotated and adjusted to a proper position, and the second screw rod 76 passes through the through chute 72 and the corresponding second mounting hole 71 and is threadedly connected to the second nut 78, the adjusting block 77 pressing against the through chute 72 will press against the limiting slide bar 73 and force it to slide adaptively, so that the limiting slide bar 73 will correspondingly slide to the most suitable position corresponding to the size of the hydrogen cylinder 4, and the pressing block 75 will cooperate to press against the hydrogen cylinder 4. This not only utilizes the characteristic of the high friction coefficient of the rubber material of the pressing block 75 to effectively prevent the hydrogen cylinder 4 from sliding, but also through a clever structural design, the pressing force changes with the adjustment of the fixed position of the second screw rod 76, greatly enhancing the stability of the hydrogen cylinder 4 in the second installation space and the third installation space, and ensuring the safety and stability of the hydrogen cylinder 4 during the flight of the drone.

[0074] Referring to Figure 9 , preferably, a positioning arc hole 11 is formed between the first support portion, the cover frame 6 and the second support portion.

[0075] This preferred embodiment designs the structure of the positioning arc hole 11, which is convenient to install this integrated fixing device onto the drone through the space of the arc hole 11. The structure is simple and easy to install and implement.

[0076] Referring to Figure 9 , preferably, the above integrated fixing device for the drone further includes a third screw rod 12 and a third nut 13, wherein:

[0077] The third screw rod 12 passes through the positioning arc hole 11 and the external drone and is threadedly connected to the third nut 13 to fasten the integrated fixing device for the drone to the external drone.

[0078] This preferred embodiment passes the third screw rod 12 through the arc hole 11 and the external drone to fasten this integrated fixing device for the drone to the drone, combining them into an integrated drone structure, providing a first installation space and a second installation space with stable position structures for the fuel cell 3 and the hydrogen cylinder 4 of the drone. The space layout is compact, the structural integrity is higher, and the protection performance for the fuel cell 3 and the hydrogen cylinder 4 against physical impacts is enhanced.

[0079] In addition, when the third screw rod 12 passes through the arc hole 11, it is also convenient to sleeved the connecting portion on the drone on it, and realize the pressing and fixing of the drone and the hydrogen energy fuel cell 3 through the third nut 13. At the same time, the pressing of the third nut 13 can press against both sides of the alternating cross-connection feature formed by the bottom frame 1 and the top frame 2 and the cover frame 6, realizing the stability of the overall installation structure.

[0080] This design comprehensively enhances the stability of the overall installation structure, ensuring that the hydrogen fuel cell 3 can always remain stable during the flight of the drone and effectively resist all kinds of vibrations and impacts.

[0081] Reference Figure 7 and Figure 8 Preferably, the cross section of the cover frame 6 is arc-shaped.

[0082] This preferred embodiment is adapted to the cover frame 6 with an arc-shaped cross-section designed for the cylindrical shell of the hydrogen bottle 4, further increasing the fitting area between the cover frame 6 and the hydrogen bottle 4, thereby enhancing the clamping force of the cover frame 6 on the hydrogen bottle 4 fixed in the second installation space, further preventing the hydrogen bottle 4 from generating relative axial displacement and radial deflection, and enhancing the structural stability of the device and the protection performance of the hydrogen bottle 4 when facing physical impact.

[0083] In a preferred embodiment, since the cross-section of the cover frame 6 is arc-shaped, that is, the through-type slide groove 72 is arc-shaped, the limiting slide bar 73 slides on the arc-shaped through-type slide groove 72, so that the pressure block 75 can adapt to the movement of the cylindrical shell surface of the hydrogen cylinder 4. The limiting slide bar 73 drives the pressure block 75 to slide in an arc, and the pressure strength can be adaptively adjusted according to the shell size of different hydrogen cylinders 4.

[0084] In a preferred embodiment, the installation process of the above hydrogen fuel cell is as follows:

[0085] First, the fuel cell 3 is installed on the top surface of the bottom frame 1, and the two hydrogen cylinders 4 are placed in the second support parts on both sides of the bottom frame 1 respectively. Subsequently, the intermittent slots 5 on the first support part of the top frame 2 and the second support part of the bottom frame 1 are staggered and inserted so that the rib structures thereof are inserted; then, the first screw rod 9 is passed through the first mounting hole 8 of the top frame 2, and is tightened with the first nut 10 to complete the limiting connection between the top frame 2 and the bottom frame 1, thereby realizing the clamping and fixation of the fuel cell 3.

[0086] Secondly, rotate the cover frame 6 connected to the first support parts on both sides of the top frame 2, so that the cover frame 6 is staggered and inserted with the intermittent slots 5 on the second support part of the bottom frame 1, so that the rib structure is inserted. According to the size of the hydrogen cylinder 4, select the appropriate second mounting hole 71 of the bottom frame 1, and pass the second screw 76 through the intersection of the through-type slide groove 72 on the side of the cover frame 6 and the selected second mounting hole 71, so as to adjust the adjustment block 77, so that the adjustment block 77 pushes the limit slide bar 73 to drive the rubber pressing block 75 to adaptively press the hydrogen cylinder 4, and then tighten the second nut 78 to fix it, so as to achieve the clamping and fixing of the hydrogen cylinder 4.

[0087] Finally, the integrated fixing device with the fuel cell 3 and the hydrogen bottle 4 is installed on the drone, the drone connecting part is put on the third screw 12 passing through the arc hole 11, and the third nut 13 is tightened to press against the interlaced structure of the bottom frame 1, the top frame 2 and the cover frame 6 to complete the overall installation.

[0088] The integrated fixing device and hydrogen fuel cell for unmanned aerial vehicles provided by the present invention have at least the following advantages compared with the prior art:

[0089] First, the unique rib structure of the bottom frame 1 and the top frame 2 is staggered and plugged. With the rib feature formed by the intermittent slot 5, the integrated and compact layout of the fuel cell 3 and the hydrogen cylinder 4 is cleverly realized. Compared with the traditional separate installation, the space occupied on the drone is greatly reduced and the overall structure is optimized. At the same time, the cover frame 6 rotatably connected on both sides of the top frame 2 cooperates with the unique rib structure of the bottom frame 1 to stagger and plug, so that the limit mechanism 7 locks the cover frame 6 and the second support part to achieve accurate and stable limiting of the hydrogen cylinder 4. This plug-in by merging the rib structure of the two frames from top to bottom improves the integrity of the fuel cell 3 and the hydrogen cylinder 4 during installation, reduces the impact of relative vibration and impact on the use of the two during the flight of the drone, ensures the stable installation of the fuel cell 3 and the hydrogen cylinder 4, enhances the reliability and safety of the drone in complex environments, and provides an innovative and practical solution for the efficient application of the drone hydrogen fuel cell 3 system.

[0090] Secondly, by passing the second screw 76 through the through-type slide groove 72 on the side of the cover frame 6 and the intersection of the slot hole 71 on the second supporting portion, the second screw 76 can be inserted into different second mounting holes 71 according to actual needs to achieve accurate fixation of the cover frame 6 after fine-tuning the rotation and optimize the fixing space of the hydrogen cylinder 4. At the same time, the adjustment blocks 77 sleeved at both ends of the second screw 76 will drive the slide bar to push the rubber pressing block 75 to press the hydrogen cylinder 4 during the tightening process of the second nut 78. This not only utilizes the high friction coefficient of the rubber pressing block 75 to effectively prevent the hydrogen cylinder 4 from sliding, but also through clever structural design, the pressing force changes with the adjustment of the fixing position of the second screw 76, which greatly enhances the stability of the two hydrogen cylinders 4 in the second installation space and the third installation space, ensuring the safety and stability of the hydrogen cylinders 4 during the flight of the drone.

[0091] Third, by providing an arc-shaped hole 11 between the first support portion of the top frame 2 at the rotation part with the cover frame 6 and the second support portion of the bottom frame 1, an exclusive space is created for the installation of the overall frame of the fuel cell 3 on the unmanned aerial vehicle. When the third screw 12 passes through the arc-shaped hole 11, the connection part of the unmanned aerial vehicle can be conveniently sleeved thereon, and the pressing and fixing are achieved by means of the third nut 13. In this process, the tightening of the third nut 13 not only shortens the distance between the bottom frame 1 and the top frame 2, but also presses tightly on the rotation part of the cover frame 6, making the alternating cross-connection structure formed by the bottom frame 1, the top frame 2, and the cover frame 6 more compact. This design comprehensively enhances the stability of the overall installation structure, ensuring that the hydrogen fuel cell 3 can always remain stable during the flight of the unmanned aerial vehicle and effectively resist various vibrations and impacts.

[0092] As used herein, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the present application. The phrase appears in various places in the specification and does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment mutually exclusive with other embodiments. Those skilled in the art will explicitly and implicitly understand that the embodiments described herein can be combined with other embodiments. For the sake of brevity of description, not all possible combinations of the various technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope recorded in this specification.

[0093] The above-described embodiments merely represent several implementation manners of the present application. The description thereof is relatively specific and detailed, but it should not be construed as a limitation on the scope of the patent of the present application. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present application, several improvements and substitutions can be made, and these improvements and substitutions should also be regarded as the protection scope of the present invention. Therefore, the protection scope of the present application shall be subject to the appended claims.

Claims

1. An integrated fixing device for a drone, characterized in that, The invention comprises a top frame, a cover frame and a bottom frame; the top frame comprises a first support portion extending from the top surface thereof to both sides; the first support portion is provided with a plurality of intermittent slots, thereby forming a rib structure; the cross section of the top frame is in an inverted U shape; the cover frame is connected to the first support portion, and the cover frame is provided with a plurality of intermittent slots, thereby forming a rib structure; the bottom frame comprises a second support portion extending from the top surface thereof to both sides; the second support portion is provided with a plurality of intermittent slots, thereby forming a rib structure; the cross section of the bottom frame is in a W shape; wherein: The first supporting part and the second supporting part are staggered and inserted to form a first installation space between the top frame and the bottom frame; The cover frame and the second support portion are staggered and inserted to form a second installation space between the cover frame and the bottom frame.

2. The one-piece fixing device for a drone according to claim 1, characterized in that, It also includes a first screw and a first nut; a first mounting hole is opened on the top surface of the top frame, and a first screw is fixed on the top surface of the bottom frame; wherein: The first screw rod passes through the first mounting hole and is threadedly connected with the first nut to fasten the top frame and the bottom frame.

3. The integrated fixing device for a drone according to claim 1, wherein The cover frame and the first supporting portion are rotatably connected.

4. The integrated fixing device for a drone according to claim 3, characterized in that, It also includes a second screw and a second nut; a through-type slide groove is opened on the side of the cover frame, and a plurality of second mounting holes are opened on the side of the second support portion; wherein: The second screw rod passes through the through-type slide groove and any second mounting hole and is threadedly connected with the second nut to fasten the cover frame and the second supporting portion.

5. The one-piece fixing device for a drone according to claim 4, characterized in that, It also includes a limiting slide bar, which is slidably connected to the through-type slide groove, and a pressing block is arranged at the bottom of the limiting slide bar.

6. The integrated fixing device for an unmanned aerial vehicle according to claim 5, characterized in that Adjustment blocks are sleeved on both ends of the second screw rod, and the adjustment blocks press against the through-type slide groove.

7. The integrated fixing device for a drone according to claim 1, characterized in that, A positioning arc hole is formed between the first supporting portion, the cover frame and the second supporting portion.

8. The integrated fixing device for a drone according to claim 7, wherein, Also includes a third screw and a third nut, wherein: The third screw rod passes through the positioning arc hole and the external drone and is threadedly connected with the third nut, so that the integrated fixing device is fastened to the external drone.

9. The one-piece fixing device for a drone according to claim 1, wherein The cross section of the cover frame is arc-shaped.

10. An integrated hydrogen fuel cell for an unmanned aerial vehicle, characterized in that, The invention comprises an integrated fixing device for a drone as claimed in any one of claims 1 to 9, a fuel cell and a hydrogen cylinder, wherein: The fuel cell is clamped and fixed in the first installation space by the top frame and the bottom frame; The hydrogen cylinder is clamped and fixed in the second installation space by the cover frame and the bottom frame; The fuel cell is connected to the hydrogen cylinder via a gas pipe.

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