Hydrogen energy unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a hydrogen energy unmanned aerial vehicle which comprises an aerial vehicle body and a protection part installed on the upper side of the aerial vehicle body, and the lower side of the protection part is fixed to the upper side of the aerial vehicle body through an electric locking structure. The lower side of the protection part is further provided with a first safety rope connected with the upper side of the aircraft body, the upper side of the protection part is concavely provided with an umbrella groove, a net plate is arranged in the umbrella groove, the lower side of the net plate is connected with the groove bottom of the umbrella groove through a second safety rope, the groove bottom of the umbrella groove is provided with an elastic piece used for popping up the net plate, and the upper side of the net plate of the umbrella cavity is provided with a parachute. A notch of the umbrella groove is provided with a safety plate used for sealing the notch of the umbrella groove, and the protection part is provided with a pop-up assembly used for popping up the safety plate at the edge of the notch of the umbrella groove. By means of separation of the aircraft body and the protection part, the situation that the parachute cannot be effectively unfolded or the parachute is caused by contact between the blades on the aircraft body and the parachute can be avoided.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically to a hydrogen-powered UAV. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft controlled by radio remote control equipment and onboard program control devices. UAVs have advantages such as small size, low cost, and ease of use.

[0003] With the continuous development of drone technology, hydrogen fuel cells are gradually becoming one of the power system choices for next-generation drones due to their advantages such as high energy density and clean emissions. However, as a high-pressure, highly flammable gaseous energy source, hydrogen fuel has an extremely high explosion limit range and extremely low ignition energy. When a drone goes out of control at high altitude, the hydrogen storage tank and hydrogen fuel cell stack are prone to falling with the drone, resulting in leakage or damage during the fall. If the leaked hydrogen comes into contact with a source of ignition or an electrical spark, it can easily ignite and cause a fire. This could not only damage the hydrogen storage tank, hydrogen fuel cell stack, and drone, but also expand the scope of damage and even threaten personnel safety. Summary of the Invention

[0004] The purpose of this invention is to provide a hydrogen-powered unmanned aerial vehicle (UAV) that solves the problem in the prior art where, when a hydrogen-powered UAV loses control at high altitude, the hydrogen storage tank and hydrogen fuel cell stack are prone to fall along with the UAV, resulting in hydrogen leakage or damage during the fall, which in turn leads to subsequent combustion and fire accidents.

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] A hydrogen-powered unmanned aerial vehicle (UAV) includes a main body and a protective section mounted on the upper side of the main body. The lower side of the protective section is fixed to the upper side of the main body via an electrically locking structure. A first safety rope connected to the upper side of the main body is also provided on the lower side of the protective section. A parachute groove is recessed on the upper side of the protective section, and a net plate is provided inside the parachute groove. The lower side of the net plate is connected to the bottom of the parachute groove via a second safety rope. An elastic element for ejecting the net plate is provided at the bottom of the parachute groove. A parachute is provided on the upper side of the net plate in the parachute cavity. A safety plate for closing the opening of the parachute groove is provided at the opening of the parachute groove. An ejection component for ejecting the safety plate is provided on the edge of the opening of the parachute groove in the protective section.

[0007] A further technical solution is that the ejection assembly includes an ejection rod, a first spring, a second spring, a first electromagnet, and a first pin. An ejection hole is recessed at the edge of the umbrella groove. A control cavity is provided near the ejection hole in the protective part. The control cavity is connected to the wall of the ejection hole via a first sliding hole. The first pin is disposed within the first sliding hole, with one end of the first pin placed inside the control cavity. A top ring is provided within the control cavity surrounding the outer wall of the first pin. The first electromagnet is installed within the control cavity. The first spring is sleeved on the outer wall of the first pin within the control cavity, with one end of the first spring abutting against the first electromagnet and the other end abutting against the top ring. The upper end of the ejection rod is connected to the lower side of the safety plate, and the lower end is placed inside the ejection hole. The upper end of the second spring abuts against the lower end of the ejection rod and the lower end abuts against the bottom of the ejection hole. A slot aligned with the first sliding hole is provided on the side wall of the ejection rod, and the end of the first pin away from the control cavity is engaged in the slot.

[0008] A further technical solution is that the electric locking structure includes an electric push rod, an insertion rod, and locking blocks. A mounting hole is provided on the lower side of the protective part. The upper part of the insertion rod is located within the mounting hole, and a locking cavity is provided inside the insertion rod. Second sliding holes communicating with the locking cavity are provided on opposite sides of the lower part of the insertion rod. Locking blocks are slidably installed in both second sliding holes. First inclined surfaces are provided on opposite sides of both locking blocks, gradually moving away from each other from bottom to top. The electric push rod is vertically installed on the top of the insertion rod within the mounting hole. The output shaft of the electric push rod passes through the locking cavity and is connected to a push block. Second inclined surfaces are provided on opposite sides of the push block, and the two second inclined surfaces slide against the two first inclined surfaces respectively. First pull grooves are recessed on opposite sides of both locking blocks, and the two first pull grooves are connected by a second spring. A locking hole is provided on the upper side of the aircraft body, and locking grooves are provided on opposite sides of the locking hole. The ends of the two locking blocks that are far apart from each other are respectively engaged in the two locking grooves.

[0009] A further technical solution is to set the sides of the locking blocks that are far apart to be curved surfaces.

[0010] A further technical solution involves an installation block on the upper edge of the mesh panel, with a launch tube inclined above the installation block. The launch tube slopes upwards away from the center of the mesh panel, and a guide tube is installed at the upper end of the launch tube. The upper end of the launch tube is connected to the guide tube via an air vent. A launch block is installed inside the guide tube, and the launch block is connected to the edge of the parachute via a first traction rope. A piston slides up and down inside the launch tube, and a push block is installed below the piston. The push block abuts against the upper side of the installation block via a third spring. The lower side of the firing tube has a vertically arranged slot through the inside and outside. A pressure plate is slidably installed in the slot. One end of the pressure plate is placed inside the firing tube and connected to the push block, and the other end is placed outside the firing tube. A fixing block is set on the upper side of the mounting block near the slot. The fixing block is aligned with the slot and has a pin hole that runs through both sides. A second pin is slidably installed in the pin hole. One end of the second pin is attached to the upper side of the pressure plate, and the other end is slidably attached to the groove wall of the umbrella groove. The end of the second pin that is slidably attached to the groove wall of the umbrella groove is connected to the groove opening of the umbrella groove by a pull rope.

[0011] A further technical solution is that a second pull groove is recessed on the upper side of the protective part at the edge of the umbrella groove, a first half-ring is provided in the second pull groove, a hook is provided at the end of the pull rope away from the second pin, the hook is connected to the first half-ring, a second half-ring is provided on the launching block, and a first traction rope is connected to the second half-ring.

[0012] A further technical solution is that the upper side of the aircraft body is recessed and has a first elastic groove and a rope groove. A fourth spring is installed in the first elastic groove. The upper end of the fourth spring abuts against the lower side of the protective part, and the lower end abuts against the bottom of the first elastic groove. A third half-ring is provided in the rope groove. A fourth half-ring is provided on the lower side of the protective part at the position corresponding to the rope groove. The third half-ring and the fourth half-ring are connected by a first safety rope.

[0013] A further technical solution is that the elastic element includes a fifth spring, and the bottom of the umbrella groove is provided with a second elastic groove. The lower end of the fifth spring abuts against the bottom of the second elastic groove, and the upper end abuts against the lower side of the mesh plate.

[0014] A further technical solution involves an installation cavity within the protective section, in which a hydrogen storage tank, a hydrogen fuel cell stack, and a control module are installed. The hydrogen storage tank is connected to the hydrogen inlet of the hydrogen fuel cell stack via a gas supply pipe, and an adjustable solenoid valve is installed on the gas supply pipe. The hydrogen fuel cell stack is electrically connected to the control module. An upper connector is located at the lower part of the protective section and is electrically connected to the control module. A lower connector is located on the upper side of the aircraft body.

[0015] Compared with the prior art, the beneficial effects of the present invention are: 1. When the unmanned aerial vehicle (UAV) loses control at high altitude, the deployment of the parachute can slow down the descent of the UAV and reduce its momentum; 2. By setting a first safety rope and an electric locking structure, the protective part can be well fixed to the upper side of the UAV body when the UAV is in normal flight. When the UAV loses control at high altitude, the separation of the UAV body and the protective part can prevent the propellers on the UAV body from contacting the parachute, thus preventing the parachute from deploying effectively or falling; 3. By setting a net plate, the parachute can be quickly ejected from the parachute slot, and air can easily pass through the net plate to enter the lower side of the parachute. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of a hydrogen-powered unmanned aerial vehicle according to the present invention.

[0017] Figure 2 This is a partial cross-sectional schematic diagram of a hydrogen-powered unmanned aerial vehicle according to the present invention.

[0018] Figure 3 for Figure 2 A magnified view of the area marked A in the middle.

[0019] Figure 4 for Figure 2 A magnified view of the area marked B.

[0020] Icons: 1-Flight body, 2-Protective section, 3-First safety rope, 4-Parachute slot, 5-Net plate, 6-Second safety rope, 7-Parachute, 8-Safety plate, 9-Ejection rod, 10-First spring, 11-Second spring, 12-First electromagnet, 13-First pin, 14-Ejection hole, 15-Control cavity, 16-First sliding hole, 17-Top ring, 18-Slot, 19-Electric push rod, 20-Insertion rod, 21-Locking block, 22-Mounting hole, 23-Locking cavity, 24-Second sliding hole, 25-First inclined surface, 26-Push block, 27-Second inclined surface, 28-First pull groove, 29-Second spring, 30-Locking hole, 31-Locking groove, 32-Mounting block, 33-Launch tube 34-Guide tube, 35-Air hole, 36-Launch block, 37-First traction rope, 38-Piston, 39-Push block, 40-Third spring, 41-Strip hole, 42-Pressure plate, 43-Fixing block, 44-Pin hole, 45-Second pin, 46-Second pull groove, 47-First half ring, 48-Hook, 49-Second half ring, 50-Pull rope, 51-First elastic groove, 52-Rope groove, 53-Fourth spring, 54-Third half ring, 55-Fourth half ring, 57-Fifth spring, 58-Second elastic groove, 59-Mounting cavity, 60-Hydrogen storage tank, 61-Upper connector, 62-Lower connector, 63-Second electromagnet, 64-Hydrogen fuel cell stack, 65-Control module, 66-Mounting bracket. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0022] Example:

[0023] like Figures 1-4As shown, a hydrogen-powered unmanned aerial vehicle (UAV) includes a main body 1 and a protective section 2 mounted on the upper side of the main body 1. The lower side of the protective section 2 is fixed to the upper side of the main body 1 via an electrically locking structure. A first safety rope 3 connected to the upper side of the main body 1 is also provided on the lower side of the protective section 2. A parachute groove 4 is recessed on the upper side of the protective section 2, and a net plate 5 is provided inside the parachute groove 4. The lower side of the net plate 5 is connected to the bottom of the groove 4 via a second safety rope 6. An elastic element for ejecting the net plate 5 is provided at the bottom of the groove 4. A parachute 7 is provided on the upper side of the net plate 5. A safety plate 8 for sealing the opening of the groove 4 is provided at the opening of the parachute groove 4. An ejection assembly for ejecting the safety plate 8 is provided at the edge of the opening of the groove 4 in the protective section 2. When the UAV loses control at high altitude, the deployment of the parachute 7 can slow down the descent of the UAV and reduce its momentum. By setting the first safety rope 3 and the electric locking structure, the protection part 2 can be well fixed to the upper side of the aircraft body 1 when the unmanned aerial vehicle is flying normally. When the unmanned aerial vehicle loses control at high altitude, the separation of the aircraft body 1 and the protection part 2 can prevent the propellers on the aircraft body 1 from contacting the parachute 7, which would prevent the parachute 7 from being effectively deployed or the parachute 7 from being deployed.

[0024] The pop-out assembly includes a pop-out rod 9, a first spring 10, a second spring 2911, a first electromagnet 12, and a first pin 13. A pop-out hole 14 is recessed at the edge of the umbrella groove 4. A control cavity 15 is provided in the protective part 2 near the pop-out hole 14. The control cavity 15 is connected to the wall of the pop-out hole 14 through a first sliding hole 16. The first pin 13 is disposed within the first sliding hole 16, with one end of the first pin 13 placed within the control cavity 15. A top ring 17 is provided within the control cavity 15, surrounding the outer wall of the first pin 13. The first electromagnet 12 is installed... Inside the control cavity 15, a first spring 10 is sleeved on the outer wall of the first pin 13. One end of the first spring 10 abuts against the first electromagnet 12, and the other end abuts against the top ring 17. The upper end of the ejector rod 9 is connected to the lower side of the safety plate 8, and the lower end is placed in the ejection hole 14. The upper end of the second spring 2911 abuts against the lower end of the ejector rod 9, and the lower end abuts against the bottom of the ejection hole 14. The side wall of the ejector rod is provided with a slot 18 aligned with the first sliding hole 16. The end of the first pin 13 away from the control cavity 15 is locked in the slot 18. When the parachute 7 is not needed, the first electromagnet 12 is not powered and does not generate magnetic attraction. With the help of the elastic force of the first spring 10, the top ring 17 is pushed, thereby inserting the first pin 13 into the slot 18 of the ejector rod. In this way, the ejector rod 9 will not eject from the ejection hole 14. At this time, the second spring 2911 is in a compressed state. When the safety plate 8 needs to be ejected, the first electromagnet 12 is powered to generate a magnetic attraction force, which attracts the first pin 13 and moves it toward the first electromagnet 12. This compresses the first spring 10, causing the first pin 13 to retract from the slot 18 back into the first sliding hole 16. In this way, the second spring 2911 can release its elastic force to push the ejection rod 9 out, so that the entire safety plate 8 can be quickly removed from the opening of the parachute slot 4. When the safety plate 8 is removed, the mesh plate 5 is ejected from the parachute slot 4 with the help of the elastic element. In this way, the parachute 7 can be ejected from the parachute slot 4 together and deployed to reduce the descent speed of the unmanned aerial vehicle.

[0025] The electric locking structure includes an electric push rod 19, an insertion rod 20, and locking blocks 21. A mounting hole 22 is provided on the lower side of the protective part 2. The upper part of the insertion rod 20 is disposed within the mounting hole 22, and a locking cavity 23 is provided within the insertion rod 20. Second sliding holes 24 communicating with the locking cavity 23 are provided on opposite sides of the lower part of the insertion rod 20. Locking blocks 21 are slidably disposed within each of the two second sliding holes 24. First inclined surfaces 25 are provided on opposite sides of each of the two locking blocks 21, and the two first inclined surfaces 25 gradually move away from each other from bottom to top. The electric push rod 19 is vertically mounted to the insertion rod within the mounting hole 22. At the top of the 20, the output shaft of the electric push rod 19 passes into the locking cavity 23 and is connected to a push block 26. Each of the opposite sides of the push block 26 has a second inclined surface 27, which slides against each of the two first inclined surfaces 25. Each of the opposite sides of the two locking blocks 21 has a first pull groove 28 recessed therein, connected by a second spring 2911. A locking hole 30 is provided on the upper side of the aircraft body 1, with locking grooves 31 on each of the opposite sides of the locking hole 30. The ends of the two locking blocks 21 that are far apart from each other are respectively engaged in the two locking grooves 31. During normal use of the unmanned aerial vehicle, the electric push rod 19 remains extended downwards. This allows the second inclined surfaces 27 on both sides of the push block 26 to push the ends of the two locking blocks 21 that are far apart from each other into the two locking grooves 31 of the locking hole 30. This fixes the lower end of the insertion rod 20 to the locking hole 30, thus securing the protective part 2 to the aircraft body 1. When the parachute 7 needs to be deployed, the electric push rod 19 retracts a certain distance, which in turn drives the push block 26 toward the attachment. Figure 4 The locking blocks 21 move upwards in the direction shown, allowing them to come closer together with the help of the second spring 2911. With the cooperation of the first inclined surface 25 and the second inclined surface 27, the two locking blocks 21 retract to the same distance, completely separating from the locking groove 31. After the locking blocks 21 separate from the locking groove 31, the insertion rod 20 can disengage from the locking hole 30, thus separating the protective part 2 from the aircraft body 1. A certain distance is maintained by the first safety rope 3 to prevent the propeller blades of the aircraft body 1 from contacting the parachute 7 and affecting it.

[0026] The sides of the locking blocks 21 that are far apart from each other are all provided with arc surfaces. The arc surfaces facilitate the locking blocks 21 to engage with the locking grooves 31 and to separate from the locking grooves 31.

[0027] A mounting block 32 is provided on the upper edge of the mesh plate 5. A launching tube 33 is inclined on the upper side of the mounting block 32. The launching tube 33 is inclined from bottom to top in a direction away from the center of the mesh plate 5. A guide tube 34 is installed at the upper end of the launching tube 33. The upper end of the launching tube 33 is connected to the guide tube 34 through an air hole 35. A launching block 36 is provided inside the guide tube 34. The launching block 36 is connected to the edge of the parachute 7 through a first traction rope 37. A piston 38 is slidably arranged inside the launching tube 33. A pushing block 39 is provided on the lower side of the piston 38. The pushing block 39 abuts against the upper side of the mounting block 32 through a third spring 40. The side of the part has a vertically extending slot 41 that runs through the inside and outside. A pressure plate 42 is slidably installed in the slot 41. One end of the pressure plate 42 is placed inside the launch tube 33 and connected to the push block 39, while the other end is placed outside the launch tube 33. A fixing block 43 is provided on the upper side of the mounting block 32 near the slot 41. The fixing block 43 is aligned with the slot 41 and has a pin hole 44 that runs through both sides. A second pin 45 is slidably installed in the pin hole 44. One end of the second pin 45 is attached to the upper side of the pressure plate 42, and the other end is slidably attached to the groove wall of the parachute slot 4. The end of the second pin 45 that is slidably attached to the groove wall of the parachute slot 4 is connected to the slot opening of the parachute slot 4 by a pull rope 50. In order to improve the deployment speed of the parachute 7, this application uses the launch block 36 to drive the edge of the parachute 7 to deploy quickly, thereby accelerating the deployment speed of the parachute 7. This is beneficial for the unmanned aerial vehicle to have the lowest safe landing distance, and can ensure the safe landing of the unmanned aerial vehicle even at low altitudes. Specifically, when the safety plate 8 has not been ejected, the pressure plate 42 is fixed by the second pin 45, causing the pressure plate 42 to drive the push block 39 to compress the third spring 40. The side of the push block 39 that contacts the third spring 40 has a compression hole to accommodate the spring. Furthermore, the end of the second pin 45 away from the pressure plate 42 is in contact with the groove wall of the parachute slot 4, preventing the second pin 45 from dislodging from the pin hole 44. When the mesh plate 5 ejects from the parachute slot 4, and the second pin 45 moves outside the parachute slot 4, the pull rope 50 pulls the second pin 45 out of the pin hole 44. Under the elastic force of the third spring 40, the push block 39 pushes the piston 38 upward, compressing air. This compressed air quickly enters the guide tube 34, pushing the launch block 36 out of the guide tube 34 at high speed. This causes the launch block 36 to rapidly deploy the edge of the parachute 7 via the first traction rope 37, enabling the parachute 7 to quickly acquire deceleration capability. With the help of the inclined launch tube 33 and the inclined second pin 45, the second pin 45 can be quickly pulled out of the pin hole 44 when the pull rope 50 pulls the second pin 45.

[0028] A second pull groove 46 is recessed at the edge of the umbrella groove 4 on the upper side of the protective part 2. A first half-ring 47 is provided in the second pull groove 46. A hook 48 is provided at the end of the pull rope 50 away from the second pin 45. The hook 48 is connected to the first half-ring 47. A second half-ring 49 is provided on the launching block 36. The first traction rope 37 is connected to the second half-ring 49. In order to improve the smoothness of pulling out the second pin 45, the diameter of the pin hole 44 is larger than the diameter of the second pin 45, and the tilt angle of the pin hole 44 and the second pin 45 is greater than 45 degrees, so as to facilitate the smooth pulling out of the second pin 45.

[0029] The upper side of the aircraft body 1 is recessed with a first elastic groove 51 and a rope groove 52. A fourth spring 53 is installed in the first elastic groove 51. The upper end of the fourth spring 53 abuts against the lower side of the protective part 2, and the lower end abuts against the bottom of the first elastic groove 51. A third half-ring 54 is provided in the rope groove 52. A fourth half-ring 55 is provided on the lower side of the protective part 2 at the position corresponding to the rope groove 52. The third half-ring 54 and the fourth half-ring 55 are connected by a first safety rope 3. With the help of the fourth spring 53, when the aircraft body 1 and the protective part 2 separate, they can be ejected and separated, thus avoiding the inability to effectively separate at the same descent speed.

[0030] The elastic element includes a fifth spring 57. A second elastic groove 58 is provided at the bottom of the parachute slot 4. The lower end of the fifth spring 57 abuts against the bottom of the second elastic groove 58, and the upper end abuts against the lower side of the mesh plate 5. The fifth spring 57 facilitates the ejection of the mesh plate 5 from the parachute slot 4. A second electromagnet 63 is also provided at the bottom of the parachute slot 4, and an adsorption block that adheres to the second electromagnet 63 is provided on the lower side of the mesh plate 5. When the first electromagnet 12 is energized, the second electromagnet 63 is also energized. This allows the second electromagnet 63 to attract the adsorption block and fix the mesh plate 5, preventing the mesh plate 5 and the safety plate 8 from ejecting simultaneously, which could cause the safety plate 8 to interfere with the deployment of the parachute 7. The power supply time to the second electromagnet 63 is controlled within 0.5 seconds, typically 0.3 seconds, ensuring timely deployment of the parachute 7 while preventing the safety plate 8 from interfering with its deployment. When the second electromagnet 63 is briefly energized and then de-energized, the fifth spring 57 will cause the mesh plate 5 to quickly pop out of the umbrella groove 4.

[0031] The protection section 2 has an installation cavity 59, which houses a hydrogen storage tank 60, a hydrogen fuel cell stack 64, and a control module 65. The hydrogen storage tank 60 is connected to the hydrogen inlet of the hydrogen fuel cell stack via a gas supply pipe, which is equipped with an adjustable solenoid valve. The hydrogen fuel cell stack 64 is electrically connected to the control module 65. An upper connector 61 is located at the lower part of the protection section 2 and is electrically connected to the control module. A lower connector 62 is located on the upper side of the aircraft body 1. This application utilizes the method of installing the hydrogen storage tank 60, hydrogen fuel cell stack 64, and control module 65 within the protection section 2. This provides effective protection for these components, ensuring their safety even in the event of a breakage of the first safety rope 3. The hydrogen storage tank 60 and the hydrogen fuel cell stack 64 are separated by a mounting bracket 66. The hydrogen storage tank 60 is mounted on the upper side of the mounting bracket 66, and the hydrogen fuel cell stack 64 is mounted on the lower side of the mounting bracket 66. The mounting bracket 66 is connected to the cavity wall of the mounting cavity 59. The first electromagnet 12 and the electromagnet mentioned in this application are both controlled by the control module 65. The upper connector 61 and the lower connector 62 facilitate the electrical connection between the hydrogen power battery 60 and the control module 65 and the aircraft body 1. This allows for the physical disconnection of the power supply to the aircraft body 1 after the aircraft body 1 and the protection part 2 are separated, thereby preventing the propeller blades from continuing to rotate and affecting the landing.

[0032] Although the invention has been described herein with reference to several illustrative embodiments, it should be understood that many other modifications and implementations can be devised by those skilled in the art, which will fall within the scope and spirit of the principles disclosed herein. More specifically, various variations and modifications can be made to the components and / or layout of the subject matter arrangement within the scope of the disclosure, drawings, and claims. Besides variations and modifications to the components and / or layout, other uses will be apparent to those skilled in the art.

Claims

1. A hydrogen-powered unmanned aerial vehicle, characterized in that, The device includes a main body (1) of an aircraft and a protective part (2) installed on the upper side of the main body (1). The lower side of the protective part (2) is fixed to the upper side of the main body (1) by an electric locking structure. The lower side of the protective part (2) is also provided with a first safety rope (3) connected to the upper side of the main body (1). The upper side of the protective part (2) is recessed and provided with a parachute groove (4). A net plate (5) is provided in the parachute groove (4). The lower side of the net plate (5) is connected to the bottom of the groove of the parachute groove (4) by a second safety rope (6). The bottom of the groove of the parachute groove (4) is provided with an elastic element for popping out the net plate (5). A parachute (7) is provided on the upper side of the net plate (5) in the parachute cavity. A safety plate (8) for closing the groove of the parachute groove (4) is provided at the opening of the parachute groove (4). The protective part (2) is provided with a pop-out component for popping out the safety plate (8) at the edge of the groove of the parachute groove (4).

2. The hydrogen-powered unmanned aerial vehicle according to claim 1, characterized in that: The pop-out assembly includes a pop-out rod (9), a first spring (10), a second spring (29) (11), a first electromagnet (12), and a first pin (13). A pop-out hole (14) is recessed at the edge of the umbrella groove (4). A control cavity (15) is provided near the pop-out hole (14) in the protective part (2). The control cavity (15) is connected to the wall of the pop-out hole (14) through a first sliding hole (16). The first pin (13) is disposed within the first sliding hole (16), with one end of the first pin (13) placed within the control cavity (15). A top ring (17) is provided within the control cavity (15) surrounding the outer wall of the first pin (13). The first electromagnet (12) is mounted on... Inside the control cavity (15), the first spring (10) is sleeved on the outer wall of the first pin (13) inside the control cavity (15). One end of the first spring (10) abuts against the first electromagnet (12), and the other end abuts against the top ring (17). The upper end of the ejector rod (9) is connected to the lower side of the safety plate (8), and the lower end is placed in the ejector hole (14). The upper end of the second spring (29) (11) abuts against the lower end of the ejector rod (9), and the lower end abuts against the bottom of the ejector hole (14). The side wall of the ejector rod is provided with a slot (18) aligned with the first sliding hole (16). The end of the first pin (13) away from the control cavity (15) is locked in the slot (18).

3. A hydrogen-powered unmanned aerial vehicle according to claim 1, characterized in that: The electric locking structure includes an electric push rod (19), an insertion rod (20), and a locking block (21). The lower side of the protective part (2) is provided with a mounting hole (22). The upper part of the insertion rod (20) is disposed in the mounting hole (22). A locking cavity (23) is provided in the insertion rod (20). The lower two sides of the insertion rod (20) are provided with second sliding holes (24) that communicate with the locking cavity (23). The locking block (21) is slidably disposed in both of the two second sliding holes (24). The two locking blocks (21) are provided with a first inclined surface (25) on opposite sides. The two first inclined surfaces (25) gradually move away from bottom to top. The electric push rod (19) is vertically installed in the mounting hole (22) on the insertion rod (21). At the top of the insert rod (20), the output shaft of the electric push rod (19) passes into the locking cavity (23) and is connected to the push block (26). The push block (26) has a second inclined surface (27) on both sides. The two second inclined surfaces (27) slide against the two first inclined surfaces (25) respectively. The two locking blocks (21) have a first pull groove (28) recessed on one side. The two first pull grooves (28) are connected by a second spring (29) (11). The upper side of the aircraft body (1) is provided with a locking hole (30). The two sides of the locking hole (30) are provided with locking grooves (31). The two locking blocks (21) are respectively locked in the two locking grooves (31) at their opposite ends.

4. A hydrogen-powered unmanned aerial vehicle according to claim 3, characterized in that: The locking blocks (21) are all set to be curved on the side that is far apart from each other.

5. A hydrogen-powered unmanned aerial vehicle according to claim 1, characterized in that: An mounting block (32) is provided on the upper edge of the mesh plate (5). A launching tube (33) is inclined on the upper side of the mounting block (32). The launching tube (33) is inclined from bottom to top in a direction away from the center of the mesh plate (5). A guide tube (34) is installed at the upper end of the launching tube (33). The upper end of the launching tube (33) is connected to the guide tube (34) through an air hole (35). A launching block (36) is provided inside the guide tube (34). The launching block (36) is connected to the edge of the parachute (7) through a first traction rope (37). A piston (38) is slidably arranged inside the launching tube (33). A pushing block (39) is provided on the lower side of the piston (38). The pushing block (39) abuts against the upper side of the mounting block (32) through a third spring (40). The lower side has a vertically arranged slot (41) that runs through the inside and outside. A pressure plate (42) is slidably arranged in the slot (41). One end of the pressure plate (42) is placed inside the launching tube (33) and connected to the pushing block (39), and the other end is placed outside the launching tube (33). A fixing block (43) is arranged on the upper side of the mounting block (32) near the slot (41). The fixing block (43) is aligned with the slot (41) and has a pin hole (44) that runs through both sides. A second pin (45) is slidably arranged in the pin hole (44). One end of the second pin (45) is attached to the upper side of the pressure plate (42), and the other end is slidably attached to the groove wall of the umbrella groove (4). The end of the second pin (45) that is slidably attached to the groove wall of the umbrella groove (4) is connected to the groove opening of the umbrella groove (4) through a pull rope (50).

6. A hydrogen-powered unmanned aerial vehicle according to claim 5, characterized in that: The upper side of the protective part (2) is recessed at the edge of the umbrella groove (4) and a second pull groove (46) is provided. A first half ring (47) is provided in the second pull groove (46). A hook (48) is provided at the end of the pull rope (50) away from the second pin (45). The hook (48) is connected to the first half ring (47). A second half ring (49) is provided on the launching block (36). The first traction rope (37) is connected to the second half ring (49).

7. A hydrogen-powered unmanned aerial vehicle according to claim 1, characterized in that: The upper side of the aircraft body (1) is recessed with a first elastic groove (51) and a rope groove (52). A fourth spring (53) is installed in the first elastic groove (51). The upper end of the fourth spring (53) abuts against the lower side of the protective part (2), and the lower end abuts against the bottom of the first elastic groove (51). A third half-ring (54) is provided in the rope groove (52). A fourth half-ring (55) is provided on the lower side of the protective part (2) at the position corresponding to the rope groove (52). The third half-ring (54) and the fourth half-ring (55) are connected by a first safety rope (3).

8. A hydrogen-powered unmanned aerial vehicle according to claim 1, characterized in that: The elastic element includes a fifth spring (57), and a second elastic groove (58) is provided at the bottom of the umbrella groove (4). The lower end of the fifth spring (57) abuts against the bottom of the second elastic groove (58), and the upper end abuts against the lower side of the mesh plate (5). A second electromagnet (63) is also provided at the bottom of the umbrella groove (4), and an adsorption block that fits against the second electromagnet (63) is provided on the lower side of the mesh plate (5).

9. A hydrogen-powered unmanned aerial vehicle according to claim 1, characterized in that: The protective part (2) is provided with an installation cavity (59), in which a hydrogen storage tank (60), a hydrogen fuel cell stack (64), and a control module (65) are installed. The hydrogen storage tank (60) is connected to the hydrogen inlet of the hydrogen fuel cell stack through a gas supply pipe. An adjustable solenoid valve is installed on the gas supply pipe. The hydrogen fuel cell stack (64) is electrically connected to the control module (65). An upper connector (61) is provided at the lower part of the protective part (2), and the upper connector (61) is electrically connected to the control module. A lower connector (62) is provided on the upper side of the aircraft body (1). The upper connector (61) and the lower connector (62) are provided.

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