Unmanned aerial vehicle integrated fixing device and hydrogen energy fuel cell

Abstract

The present application relates to the technical field of aircraft fuel cell device, particularly relates to a kind of unmanned aerial vehicle integrated fixing device and hydrogen energy fuel cell.The device is inserted into the stable integrated structure by the unique rib structure comprising a plurality of intermittent slots, the top frame, cover frame and bottom frame are staggered, to provide the first installation space and the second installation space of position structure stability for fuel cell and hydrogen cylinder, so that fuel cell and hydrogen cylinder fixed in the first installation space and the second installation space respectively cannot produce relative axial displacement and radial deflection, improve its structural stability and anti-interference for complex environmental factors;And compared with the separate mounting design of prior art, the device does not need to rely on bolt, buckle and several miscellaneous mechanical fasteners to position fuel cell and hydrogen cylinder, and the fixing mode is simple;Fuel cell and hydrogen cylinder are fastened in the integrated fixing device simultaneously, and the space layout is compact, and the structural integrity is higher.

Description

TECHNICAL FIELD

[0001] The present application 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. BACKGROUND

[0002] At present, the application of unmanned aerial vehicle equipment in the technical fields of aerial photography, logistics distribution, surveying and mapping, agricultural plant protection, etc. is gradually deepening. The endurance and charging capacity of traditional lithium battery powered unmanned aerial vehicles have been unable to meet the long distance and long time operation requirements of related technical fields. Therefore, hydrogen energy fuel cells, with their high energy density, long endurance, environmental protection and other advantages, have gradually become the research and development direction of unmanned aerial vehicle energy technology field.

[0003] Due to the limitations of technology development, the fuel cell and hydrogen cylinder of the existing unmanned aerial vehicle are designed in a separate installation. On the one hand, this design occupies a large space, has a scattered layout, affects the compactness of the unmanned aerial vehicle structure, and leads to a decline in the flight performance of the unmanned aerial vehicle. On the other hand, this design relies on a plurality of miscellaneous mechanical fasteners such as bolts and buckles to position the fuel cell and hydrogen storage cylinder in a split body. The installation steps are cumbersome and the reliability is insufficient. In the process of unmanned aerial vehicle flight, in the case of unmanned aerial vehicle vibration or attitude mutation caused by air flow disturbance or physical impact, the separate design is prone to cause the relative axial displacement and radial deflection of the fuel cell and hydrogen cylinder, which causes the mechanical fasteners to loosen and the hydrogen transmission pipeline to repeatedly bear stress deformation and loosen, affecting the stability of energy supply and existing gas tightness failure risk. The above problems seriously restrict the practical process of hydrogen energy unmanned aerial vehicle in long-haul operation scenarios. SUMMARY

[0004] The present application aims to provide an unmanned aerial vehicle integrated fixing device and a hydrogen energy fuel cell, which forms a stable integrated structure of the fuel cell and the hydrogen cylinder, and improves the safety of the hydrogen energy fuel cell of the unmanned aerial vehicle, to solve the technical problem that the existing separate design is prone to cause the relative axial displacement and radial deflection of the fuel cell and the hydrogen cylinder.

[0005] In order to achieve the above-mentioned purpose, the first aspect of the present application provides an unmanned aerial vehicle integrated fixing device, comprising 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 insertion slots, thereby forming a rib structure; the cross section of the top frame is inverted U-shaped; the cover frame is connected with the first support portion, and the cover frame is provided with a plurality of intermittent insertion 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 insertion slots, thereby forming a rib structure; the cross section of the bottom frame is w-shaped; wherein:

[0006] The first support portion and the second support portion are interlocked to form a first mounting space between the top frame and the bottom frame; the cover frame and the second support portion are interlocked to form a second mounting space between the cover frame and the bottom frame.

[0007] The aforementioned integrated UAV mounting device utilizes a unique rib structure with multiple intermittent slots to interlock the top frame, cover frame, and bottom frame, forming a stable integrated structure. This provides a stable first and second mounting space for the fuel cell and hydrogen cylinder, preventing relative axial displacement and radial deflection of the fuel cell and hydrogen cylinder, which are respectively fixed in the first and second mounting spaces. This enhances the structural stability and anti-interference capabilities against complex environmental factors. Compared to the separate installation design of existing technologies, this device eliminates the need for bolts, clips, and other miscellaneous mechanical fasteners to position the fuel cell and hydrogen cylinder, simplifying the fixing method. The fuel cell and hydrogen cylinder are simultaneously secured within this integrated mounting device, resulting in a compact spatial layout, higher structural integrity, and enhanced protection for the fuel cell and hydrogen cylinder against physical impacts.

[0008] Preferably, the integrated UAV fixing device further includes a first screw and a first nut, the top surface of the top frame has a first mounting hole, and the top surface of the bottom frame is fixed with the first screw; wherein:

[0009] The first screw passes through the first mounting hole and is threaded into the first nut to secure 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 this integrated fixing device. At the same time, the length of the second screw can affect the size of the first mounting space formed by the top frame and the bottom frame. Users can select a second screw of appropriate length for fuel cells of different sizes, making the device more widely applicable.

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

[0012] This preferred embodiment enables the device to adjust the position of the cover frame for hydrogen cylinders of different sizes, thereby adjusting the size of the second mounting space to accommodate hydrogen cylinders of different shapes and expanding the applicability of the device. At the same time, after the hydrogen cylinder is fixed in the second mounting space, the device can increase the clamping force on the hydrogen cylinder by rotating the position of the cover frame, further preventing the hydrogen cylinder from undergoing relative axial displacement and radial deflection, thus enhancing the structural stability of the device and its protective performance against physical impacts on the hydrogen cylinder.

[0013] Preferably, the unmanned aerial vehicle integrated fixing device further comprises a second screw rod and a second nut; the cover frame is provided with a through sliding groove on the side surface, and the second supporting part is provided with a plurality of second mounting holes on the side surface; wherein:

[0014] The second screw rod is threadedly connected with the second nut after penetrating through the through sliding groove and any second mounting hole, so as to fasten the cover frame and the second supporting part.

[0015] It should be noted that the cover frame and the second supporting part are both rib structures, which include a plurality of parallel ribs, and each two ribs are provided with intermittent slot spaces. Therefore, the cover frame is provided with a through sliding groove on the side surface, which should be understood as that each rib of the cover frame is provided with the same through sliding groove on the side surface, and the second supporting part is provided with a plurality of second mounting holes on the side surface, which should be understood as that each rib of the second supporting part is provided with the same plurality of second mounting holes on the side surface. For the convenience of understanding and description, the application briefly describes the above structure as the through sliding groove on the side surface of the cover frame and the plurality of second mounting holes on the side surface of the second supporting part.

[0016] The preferred embodiment cooperates with the cover frame rotating mechanism to provide a plurality of second mounting holes on the side surface of the second supporting part. For hydrogen cylinders with different sizes, when the cover frame is adjusted to the appropriate position, the through sliding groove will be aligned with the corresponding second mounting hole at this position, and the second screw rod can be threadedly connected with the second nut after penetrating through the through sliding groove and the corresponding second mounting hole, so as to fasten the cover frame and the second supporting part, keep the second installation space at the current adjustment size, and complete the locking and fastening of the hydrogen cylinder in the second installation space.

[0017] Preferably, the unmanned aerial vehicle integrated fixing device further comprises a limiting sliding strip, which is in sliding connection with the through sliding groove, and the bottom of the limiting sliding strip is provided with a pressing block.

[0018] The preferred embodiment cooperates with the cover frame rotating mechanism to slide the limiting sliding strip at the through sliding groove. When the second installation space is fixed with a hydrogen cylinder, the limiting sliding strip can slide in the through sliding groove in cooperation with the rotation of the cover frame, and the pressing block provided at the bottom of the limiting sliding strip can cooperate with the sliding of the limiting sliding strip to press and limit the hydrogen cylinder in the second installation space; when the cover frame is rotated to the most appropriate position corresponding to the size of the hydrogen cylinder, the limiting sliding strip is correspondingly slid to the most appropriate position corresponding to the size of the hydrogen cylinder, so that the pressing block cooperates with the pressing of the hydrogen cylinder to apply sufficient pressure to the hydrogen cylinder, and the locking and fastening of the hydrogen cylinder are completed.

[0019] Preferably, the second screw rod is provided with an adjusting block at both ends, and the adjusting block presses the through sliding groove.

[0020] The preferred embodiment cooperates with the cover frame rotating mechanism and the limiting sliding bar sliding mechanism, and the second screw rod is sleeved with an adjusting block at both ends. When the cover frame is adjusted to the appropriate position, the second screw rod is screwed with the second nut after penetrating the through sliding groove and the corresponding second mounting hole, and the adjusting block pressing against the through sliding groove will press against the limiting sliding bar and force it to adaptively slide, so that the limiting sliding bar is correspondingly slid to the most appropriate position corresponding to the size of the hydrogen cylinder, and the pressing block is matched to press against the hydrogen cylinder to apply sufficient pressure to the hydrogen cylinder, thereby completing the locking and fastening of the hydrogen cylinder.

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

[0022] The preferred embodiment designs a positioning arc hole structure, which facilitates the installation of the integrated fixing device to the unmanned aerial vehicle or other equipment through the arc hole space, and has a simple structure and is easy to install.

[0023] Preferably, the unmanned aerial vehicle integrated fixing device further comprises a third screw rod and a third nut, wherein:

[0024] The third screw rod penetrates the positioning arc hole and the external unmanned aerial vehicle and is screwed with the third nut, so as to fasten the unmanned aerial vehicle integrated fixing device with the external unmanned aerial vehicle.

[0025] The preferred embodiment penetrates the arc hole with the third screw rod and the external unmanned aerial vehicle, so as to fasten the integrated fixing device with the unmanned aerial vehicle, and combines the unmanned aerial vehicle structure, thereby providing the first installation space and the second installation space for the fuel cell and the hydrogen cylinder of the unmanned aerial vehicle, which has a compact space layout and higher structural integrity, and enhances the protection performance of the fuel cell and the hydrogen cylinder when facing physical impact.

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

[0027] The preferred embodiment is adapted to the cylindrical shell of the hydrogen cylinder, and the cross section of the cover frame is arc-shaped, which further increases the fitting area of the cover frame and the hydrogen cylinder, thereby improving 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 of the hydrogen cylinder when facing physical impact.

[0028] The second aspect of the present application provides an unmanned aerial vehicle integrated hydrogen energy fuel cell, comprising the unmanned aerial vehicle integrated fixing device, the fuel cell and the hydrogen cylinder according to any one of the first aspect of the present application, 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 a gas pipe.

[0032] The integrated hydrogen fuel cell fixes the fuel cell and the hydrogen cylinder in an integrated fixing device of a UAV, compared with the traditional separated installation design, the design can form an integrated structure of the fuel cell and the hydrogen cylinder, and the two will not have relative axial displacement and radial deflection, thereby improving the structural stability and anti-interference of the hydrogen fuel cell to complex environmental factors, and enhancing the defense capability against physical impact. BRIEF DESCRIPTION OF DRAWINGS

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

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

[0035] Figure 3 is a three-dimensional structure schematic diagram of an overall frame body of a UAV integrated fixing device provided by an embodiment of the present application;

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

[0037] Figure 5 is a three-dimensional structure schematic diagram of a top frame and a cover frame of a UAV integrated fixing device provided by an embodiment of the present application;

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

[0039] Figure 7 is a three-dimensional structure bottom view schematic diagram of a top frame and a cover frame of a UAV integrated fixing device provided by an embodiment of the present application;

[0040] Figure 8 is a three-dimensional structure schematic diagram of a cover frame of a UAV integrated fixing device provided by an embodiment of the present application;

[0041] Figure 9 is a three-dimensional structure partial schematic diagram of a UAV integrated fixing device provided by an embodiment of the present application;

[0042] Figure 10It is a part A enlarged perspective structural schematic view of an unmanned aerial vehicle integrated fixing device provided by the embodiment of the application.

[0043] Figure 11 It is a limiting mechanism part structural schematic view of an unmanned aerial vehicle integrated fixing device provided by the embodiment of the application.

[0044] Figure 12 It is another limiting mechanism part structural schematic view of an unmanned aerial vehicle integrated fixing device provided by the embodiment of the application.

[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 type sliding groove; 73, limiting sliding strip; 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 DESCRIPTION

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

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

[0048] 1) Unmanned aerial vehicle: Unmanned aerial vehicle technology (Unmanned Aerial Vehicle, UAV) is a high complexity system with unmanned aerial vehicle as the core, integrating aeronautical dynamics, automatic control, information sensing and communication navigation, etc.

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

[0050] With the wide application of unmanned aerial vehicles (UAVs) in aerial photography, logistics distribution, surveying and mapping, agricultural plant protection and other fields, higher requirements for the endurance and energy utilization efficiency of the UAVs are put forward in the related fields. The traditional lithium battery powered UAVs have problems such as short endurance time and long charging time, which are difficult to meet the demand of long distance and long time operation. Therefore, hydrogen fuel cell gradually becomes a research hotspot in the field of UAV energy with its advantages of high energy density, long endurance and environmental protection.

[0051] Due to the limitation of technology development, the existing hydrogen fuel cell system structure of the UAV has many problems. On the one hand, the current fuel cell and hydrogen cylinder of the UAV are designed in a separated manner, which leads to that the fuel cell and the hydrogen cylinder occupy too much internal space of the UAV and are dispersedly arranged, thereby affecting the overall structural compactness and flight performance of the UAV. On the other hand, the existing installation method often positions the battery and the hydrogen cylinder through multiple parts, which is not convenient to install and is difficult to reliably fix. During the flight of the UAV, due to factors such as vibration and impact, the fuel cell and the hydrogen cylinder may be easily loosened and displaced due to the dispersed installation, thereby affecting the stability of energy supply and even causing safety problems.

[0052] In order to solve the above technical problems, with reference to Figure 1 and Figure 2 , the embodiment of the present application provides a UAV integrated hydrogen fuel cell, which comprises a UAV integrated fixing device, a fuel cell 3 and two hydrogen cylinders 4.

[0053] With reference to Figure 2 , Figure 3 , Figure 5 , Figure 6 and Figure 7 , the top frame 2 comprises a first support part extending from the top surface thereof to both sides; the first support part is provided with a plurality of intermittent insertion grooves 5, thereby forming a rib structure; the cross section of the top frame 2 is in an inverted U shape; two cover frames 6 are connected to both sides of the top frame 2 and the first support part, respectively; the cover frame 6 is provided with a plurality of intermittent insertion grooves 5, thereby forming a rib structure.

[0054] With reference to Figures 2-4 , the bottom frame 1 comprises a second support part extending from the top surface thereof to both sides; the second support part is provided with a plurality of intermittent insertion grooves 5, thereby forming a rib structure; the cross section of the bottom frame 1 is in a w shape.

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

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

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

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

[0059] The above unmanned aerial vehicle integrated hydrogen energy fuel cell is formed by a unique rib structure containing a plurality of intermittent slots 5, the top frame 2, the cover frame 6 and the bottom frame 1 are staggered and inserted together to form a stable integrated structure, thereby providing the fuel cell 3 and the hydrogen cylinder 4 with a first installation space and a second installation space with stable position structure, so that the fuel cell 3 and the hydrogen cylinder 4 fixed in the first installation space and the second installation space respectively cannot produce relative axial displacement and radial deflection, thereby improving the structural stability and anti-interference of the fuel cell 3 and the hydrogen cylinder 4 under the influence of complex environmental factors; compared with the separate installation design of the prior art, the device does not need to rely on a plurality of miscellaneous mechanical fasteners such as bolts and buckles to position the fuel cell 3 and the hydrogen cylinder 4, and the fixing method is simple; the fuel cell 3 and the hydrogen cylinder 4 are simultaneously fastened in the unmanned aerial vehicle integrated fixing device, the space layout is compact, the structural integrity is higher, and the protection performance of the fuel cell 3 and the hydrogen cylinder 4 when facing physical impact is enhanced.

[0060] Referring to Figures 1-6 , preferably, the unmanned aerial vehicle integrated fixing device further comprises a first screw 9 and a first nut 10, two first mounting holes 8 are opened on the top surface of the top frame 2, and two first screws 9 are fixed on the top surface of the bottom frame 1 corresponding to the two first mounting holes 8; wherein:

[0061] The first screw 9 is threaded with the corresponding first nut 10 after penetrating the corresponding first mounting hole 8, so as to fasten the top frame 2 and the bottom frame 1.

[0062] The preferred embodiment further uses the first screw rod 9 to enhance the connection tightness of the top frame 2 and the bottom frame 1, and improve the stability of the unmanned aerial vehicle integrated fixing device. Meanwhile, the length of the second screw rod 76 can affect the size of the first installation space formed by the top frame 2 and the bottom frame 1, and users can select the second screw rod 76 with a suitable length according to the size of the fuel cell 3, so that the device has a wider application range. In addition, the two first screw rods 9 further limit the fuel cell 3 in the first installation space to prevent the fuel cell 3 from slipping off.

[0063] Preferably, the cover frame 6 and the first support part are rotationally connected.

[0064] The preferred embodiment enables the device to rotationally adjust the position of the cover frame 6 according to the size of the hydrogen cylinder 4, so as to adjust the size of the second installation space, so that it is suitable for hydrogen cylinders 4 of different shapes, and improves the application range of the device. Meanwhile, after the hydrogen cylinder 4 is fixed in the second installation space, the position of the cover frame 6 can be adjusted by rotation, so as to improve the clamping force of the device on the hydrogen cylinder 4, further prevent the hydrogen cylinder 4 from generating relative axial displacement and radial deflection, and enhance the structural stability of the device and the protection performance of the hydrogen cylinder 4 when facing physical impact.

[0065] Referring to Figures 9-10 , Figure 10 is an enlarged perspective structural schematic view of part A of the unmanned aerial vehicle integrated fixing device provided by the embodiment of the present application. Preferably, the unmanned aerial vehicle integrated fixing device further comprises a limiting mechanism 7, the limiting mechanism 7 comprises a second screw rod 76 and a second nut 78; the cover frame 6 is provided with a through-type sliding groove 72 on the side surface, and the second support part is provided with a plurality of second mounting holes 71 on the side surface; wherein:

[0066] The second screw rod 76 is threadedly connected with the second nut 78 after penetrating through the through-type sliding groove 72 and any second mounting hole 71, so as to fasten the cover frame 6 and the second support part.

[0067] It should be noted that since the cover frame 6 and the second support part are both rib structures, which include a plurality of parallelly distributed ribs, and each two ribs are provided with intermittent insertion grooves 5 therebetween. Therefore, the cover frame 6 is provided with the same through-type sliding groove 72 on the side surface of each rib, and the second support part is provided with the same plurality of second mounting holes 71 on the side surface of each rib. For the convenience of understanding and description, the present application briefly describes the through-type sliding groove 72 provided on the side surface of the cover frame 6 and the plurality of second mounting holes 71 provided on the side surface of the second support part.

[0068] The preferred embodiment cooperates with the cover frame 6 rotating mechanism to open several second mounting holes 71 on the side of the second support part. For hydrogen cylinders 4 of different sizes, when the cover frame 6 is adjusted to the appropriate position, the through sliding groove 72 will be aligned with the corresponding second mounting hole 71, and the second screw 76 can pass through the through sliding groove 72 and the corresponding second mounting hole 71 and be screwed with the second nut 78, thereby achieving the fastening of the cover frame 6 and the second support part, keeping the second installation space at the size at the moment, and completing the locking and fastening of the hydrogen cylinder 4 in the second installation space.

[0069] With reference to Figure 7 , Figure 8 , Figure 11 and Figure 12 , preferably, the limiting mechanism 7 further comprises two limiting sliding strips 73, and the two limiting sliding strips 73 are respectively in sliding connection with the through sliding groove 72. The bottom of each limiting sliding strip 73 is connected to the pressing block 75 through the connecting block 74.

[0070] The preferred embodiment cooperates with the cover frame 6 rotating mechanism to slide the limiting sliding strip 73 at the through sliding groove 72. When the second installation space is fixed with the hydrogen cylinder 4, the two limiting sliding strips 73 can slide in the through sliding groove 72 in cooperation with the rotation of the cover frame 6, and at this time, the two pressing blocks 75 at the bottom of the two limiting sliding strips 73 will cooperate with the sliding of the limiting sliding strip 73 to jointly 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 appropriate position corresponding to the size of the hydrogen cylinder 4, the limiting sliding strip 73 is correspondingly slid to the most appropriate position corresponding to the size of the hydrogen cylinder 4, so that the two pressing blocks 75 jointly press the hydrogen cylinder 4 from two directions to exert sufficient pressure on it, thereby completing the locking and fastening of the hydrogen cylinder 4.

[0071] In a preferred embodiment, the pressing block 75 is made of rubber material. Rubber material has a high friction coefficient, and the use of 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] With reference to Figures 9-11 , preferably, the second screw 76 is sleeved with an adjusting block 77 at both ends, and the adjusting block 77 presses the through sliding groove 72.

[0073] The preferred embodiment cooperates with the cover frame 6 rotating mechanism and the limiting sliding strip 73 sliding mechanism, and the second screw rod 76 is sleeved with an adjusting block 77 at both ends. When the cover frame 6 is adjusted to the appropriate position, the second screw rod 76 is threaded with the second nut 78 after penetrating the through sliding groove 72 and the corresponding second mounting hole 71, and the adjusting block 77 pressing against the through sliding groove 72 will press against the limiting sliding strip 73 and force it to adaptively slide, so that the limiting sliding strip 73 is correspondingly matched to the most suitable position corresponding to the size of the hydrogen cylinder 4, and the pressing block 75 is matched to press against the hydrogen cylinder 4. Not only does this effectively prevent the hydrogen cylinder 4 from sliding by utilizing the high friction coefficient of the rubber material of the pressing block 75, but also changes the pressing force by adjusting the fixed position of the second screw rod 76 through ingenious structural design, greatly enhancing the stability of the hydrogen cylinder 4 in the second installation space and the third installation space, ensuring the safety and stability of the hydrogen cylinder 4 during the flight of the unmanned aerial vehicle.

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

[0075] The preferred embodiment designs the positioning arc hole 11 structure, which facilitates the installation of the integrated fixing device to the unmanned aerial vehicle through the arc hole 11 space, and has a simple structure and is easy to install.

[0076] Referring to Figure 9 , preferably, the integrated fixing device of the unmanned aerial vehicle further comprises a third screw rod 12 and a third nut 13, wherein:

[0077] The third screw rod 12 penetrates the positioning arc hole 11 and the external unmanned aerial vehicle and is threaded with the third nut 13, so that the integrated fixing device of the unmanned aerial vehicle is fastened with the external unmanned aerial vehicle.

[0078] The preferred embodiment penetrates the arc hole 11 with the third screw rod 12 and the external unmanned aerial vehicle, so that the integrated fixing device of the unmanned aerial vehicle is fastened with the unmanned aerial vehicle, and the unmanned aerial vehicle structure is integrated, providing the first installation space and the second installation space for the fuel cell 3 and the hydrogen cylinder 4, which have stable position structure, compact space layout and higher structural integrity, and enhances the protection performance of the fuel cell 3 and the hydrogen cylinder 4 when facing physical impact.

[0079] In addition, the third screw rod 12 penetrates the arc hole 11, which is convenient for sleeving the connecting part on the unmanned aerial vehicle, and realizes the pressing and fixing of the unmanned aerial vehicle and the hydrogen fuel cell 3 through the third nut 13, and the third nut 13 can press tightly on both sides of the interlaced connection feature formed by the bottom frame 1, the top frame 2 and the cover frame 6, realizing the stability of the overall installation structure.

[0080] This design enhances the stability of the overall installation structure in all directions, ensuring that the hydrogen fuel cell 3 remains stable during the flight of the unmanned aerial vehicle and effectively resists various vibrations and impacts.

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

[0082] This preferred embodiment is suitable for a hydrogen cylinder 4 with a cylindrical shell design and an arc-shaped cover frame 6, further increasing the contact area between the cover frame 6 and the hydrogen cylinder 4, thereby enhancing the clamping force of the cover frame 6 on the hydrogen cylinder 4 fixed in the second installation space, further preventing the hydrogen cylinder 4 from producing relative axial displacement and radial deflection, and enhancing the structural stability of the device and the protection performance of the hydrogen cylinder 4 when subjected to physical impact.

[0083] In a preferred embodiment, since the cross-section of the cover frame 6 is arc-shaped, i.e., the through sliding groove 72 is arc-shaped, and the limiting sliding bar 73 slides on the arc-shaped through sliding groove 72, the abutting block 75 can adapt to the movement of the cylindrical shell surface of the hydrogen cylinder 4. By driving the abutting block 75 to slide arcuately through the limiting sliding bar 73, the abutting force can be adjusted adaptively according to the shell size of different hydrogen cylinders 4.

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

[0085] First, install the fuel cell 3 on the top surface of the bottom frame 1, place two hydrogen cylinders 4 in the second support portions on both sides of the bottom frame 1, then interleave the intermittent insertion slots 5 on the first support portions of the top frame 2 with the second support portions of the bottom frame 1 to make the rib structures fit together, then pass the first screw 9 through the first installation hole 8 of the top frame 2 and tighten it with the first nut 10 to complete the limiting connection of the top frame 2 and the bottom frame 1, and achieve the clamping and fixing of the fuel cell 3.

[0086] Second, rotate the cover frame 6 connected to the first support portions on both sides of the top frame 2, and interleave the cover frame 6 with the intermittent insertion slots 5 on the second support portions of the bottom frame 1 to make the rib structures fit together. According to the size of the hydrogen cylinder 4, select the appropriate second installation hole 71 of the bottom frame 1, pass the second screw 76 through the through sliding groove 72 on the side of the cover frame 6 and the intersection of the selected second installation hole 71, thereby adjusting the adjusting block 77, making the adjusting block 77 push the limiting sliding bar 73 to drive the rubber abutting block 75 to adaptively abut against the hydrogen cylinder 4, and then tighten the second nut 78 to fix it, achieving the clamping and fixing of the hydrogen cylinder 4.

[0087] Finally, the integrated fixing device with fuel cell 3 and hydrogen cylinder 4 is installed on the UAV, the UAV connecting part is sleeved on the third screw 12 penetrating the arc hole 11, the third nut 13 is tightened, and the interlaced structure of the bottom frame 1, the top frame 2 and the cover frame 6 is tightly contacted, and the overall installation is completed.

[0088] The unmanned aerial vehicle integrated fixing device and hydrogen energy fuel cell provided by the application has at least the following advantages compared with the prior art:

[0089] First, the bottom frame 1 and the top frame 2 are interlaced with the unique rib structure, and the rib features formed by the intermittent slot 5 are used to achieve the integrated and compact layout of the fuel cell 3 and the hydrogen cylinder 4. Compared with the traditional separate installation, the space occupation on the UAV is greatly reduced, and the overall structure is optimized. At the same time, the cover frame 6 on both sides of the top frame 2 is rotatably connected, and the cover frame 6 is interlaced with the unique rib structure of the bottom frame 1 to limit the locking of the cover frame 6 and the second support part, so as to realize the accurate and stable limiting of the hydrogen cylinder 4. This interlacing of the rib structures of the two frame bodies improves the integrity of the fuel cell 3 and the hydrogen cylinder 4 during installation, reduces the influence of relative vibration and impact of the two during UAV flight, ensures the stable installation of the fuel cell 3 and the hydrogen cylinder 4, and enhances the reliability and safety of the UAV in complex environments. An innovative and practical solution is provided for efficient application of the UAV hydrogen energy fuel cell 3 system.

[0090] Second, the second screw 76 penetrates the intersection of the second installation hole 71 and the slot hole of the second support part on the side through type sliding groove 72 of the cover frame 6. According to actual needs, the second screw 76 can be inserted into different second installation holes 71 to realize accurate fixing after the cover frame 6 is finely adjusted, and the fixing space of the hydrogen cylinder 4 is optimized. At the same time, the adjusting block 77 sleeved on both ends of the second screw 76 will drive the sliding strip and push the rubber pressure block 75 to press the hydrogen cylinder 4 during the tightening process of the second nut 78. This not only effectively prevents the hydrogen cylinder 4 from sliding by using the high friction coefficient of the rubber pressure block 75, but also changes the pressure degree by adjusting the fixed position of the second screw 76 through ingenious structure design, greatly enhancing the stability of the two hydrogen cylinders 4 in the second installation space and the third installation space, and ensuring the safety and stability of the hydrogen cylinder 4 during UAV flight.

[0091] Third, by setting an arc hole 11 between the first support part of the top frame 2 and the rotation point of the cover frame 6 and the second support part of the bottom frame 1, a dedicated space is created for the installation of the entire frame of the fuel cell 3 on the drone. When the third screw 12 passes through the arc hole 11, the drone connection part can be easily fitted onto it, and the third nut 13 is used to achieve pressure fixation. In this process, the tightening of the third nut 13 not only brings the distance between the bottom frame 1 and the top frame 2 closer, but also tightens the rotation point of the cover frame 6, making the interlocking 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 drone and effectively resist various vibrations and impacts.

[0092] The term "embodiment" as used herein means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a mutually exclusive, independent, or alternative embodiment. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described; however, any combination of these technical features that does not contradict each other should be considered within the scope of this specification.

[0093] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this application. It should be noted that those skilled in the art can make various improvements and substitutions without departing from the concept of this application, and these improvements and substitutions should also be considered within the scope of protection of this invention. Therefore, the scope of protection of this application should be determined by the appended claims.

Claims

1. An integrated fixing device for unmanned aerial vehicles (UAVs), characterized in that, The system includes a top frame, a cover frame, and a bottom frame. The top frame includes a first support portion extending from its top surface to both sides. The first support portion has several intermittent slots, forming a rib structure. The top frame has an inverted U-shaped cross-section. The cover frame is connected to the first support portion and has several intermittent slots, forming a rib structure. The bottom frame includes a second support portion extending from its top surface to both sides. The second support portion has several intermittent slots, forming a rib structure. The bottom frame has a W-shaped cross-section. Wherein: The first support portion and the second support portion are interlocked to form a first mounting space between the top frame and the bottom frame; The cover frame and the second support are interlocked to form a second mounting space between the cover frame and the bottom frame.

2. The integrated fixing device for unmanned aerial vehicles according to claim 1, characterized in that, It also includes a first screw and a first nut; the top surface of the top frame has a first mounting hole, and the top surface of the bottom frame is fixed with the first screw; wherein: The first screw passes through the first mounting hole and is threaded into the first nut to secure the top frame and the bottom frame.

3. The integrated fixing device for unmanned aerial vehicles according to claim 1, characterized in that, The cover frame and the first support are rotatably connected.

4. The integrated fixing device for unmanned aerial vehicles according to claim 3, characterized in that, It also includes a second screw and a second nut; the cover frame has a through-type sliding groove on its side, and the second support part has several second mounting holes on its side; wherein: The second screw passes through the through-type slide and any of the second mounting holes and is threadedly connected to the second nut to fasten the cover and the second support.

5. The integrated fixing device for unmanned aerial vehicles 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 provided at the bottom of the limiting slide bar.

6. The integrated fixing device for unmanned aerial vehicles according to claim 5, characterized in that, Adjusting blocks are fitted at both ends of the second screw, and the adjusting blocks press against the through-type sliding groove.

7. The integrated fixing device for unmanned aerial vehicles according to claim 1, characterized in that, A positioning arc hole is formed between the first support part, the cover frame and the second support part.

8. The integrated fixing device for unmanned aerial vehicles according to claim 7, characterized in that, It also includes a third screw and a third nut, wherein: The third screw passes through the positioning arc hole and the external drone and is threadedly connected to the third nut to secure the integrated fixing device to the external drone.

9. The integrated fixing device for unmanned aerial vehicles according to claim 1, characterized in that, The cross-section of the cover is arc-shaped.

10. An integrated hydrogen fuel cell for unmanned aerial vehicles, characterized in that, Includes the integrated unmanned aerial vehicle (UAV) mounting device, fuel cell, and hydrogen cylinder as described in any one of claims 1 to 9, wherein: The fuel cell is clamped and fixed in the first mounting space by the top frame and the bottom frame; The hydrogen cylinder is clamped and fixed in the second mounting space by the cap frame and the bottom frame; The fuel cell is connected to the hydrogen cylinder via a gas pipe.

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