Hydrogen fuel protection device of hydrogen fuel cell for unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a hydrogen fuel protection device of a hydrogen fuel cell for an unmanned aerial vehicle, which comprises an unmanned aerial vehicle, and a hydrogen fuel tank and a hydrogen fuel cell arranged on the unmanned aerial vehicle; the hydrogen fuel tank is detachably arranged at the top of the unmanned aerial vehicle through the upper protection module; the upper protection module is provided with a protective cover for protecting the hydrogen fuel tank in real time and an active protection unit for actively separating the protective cover from the unmanned aerial vehicle in a protection state; the hydrogen fuel cell is detachably arranged below the unmanned aerial vehicle through the lower protection module; the lower protection module is provided with a buffer rack for comprehensively protecting the hydrogen fuel cell in a protection state; according to the invention, the hydrogen fuel tank can be detected in real time and can be comprehensively protected.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to a hydrogen fuel protection device for a hydrogen fuel cell used in an unmanned aerial vehicle. Background Art

[0002] In the context of the continuous development of unmanned aerial vehicle technology, hydrogen fuel cells have gradually become one of the power system options for the new generation of unmanned aerial vehicles due to their high energy density, clean emissions, and other advantages. However, as a high-pressure and highly flammable gas energy source, hydrogen fuel has a high leakage risk during actual use. Especially during the flight of an unmanned aerial vehicle, due to the continuous flight of the unmanned aerial vehicle, hydrogen fuel tank leakage may occur due to high-pressure system leakage, interface leakage, or mechanical vibration. This not only may lead to fuel waste, but also may cause serious structural safety hazards. Especially when the leakage occurs at any side position of the fuel tank, the leaked hydrogen will spray out from the leakage point at high speed, generating an asymmetric thrust on the unmanned aerial vehicle due to uneven force directions, thus causing problems such as flight yaw and attitude instability, seriously affecting the flight control and operation accuracy of the unmanned aerial vehicle.

[0003] In addition, due to hydrogen having an extremely wide explosion limit range and an extremely low ignition energy, when the leakage concentration accumulates to reach the critical explosion range, it is extremely easy to trigger a combustion and explosion accident if exposed to a fire source or an electric spark. This not only may cause damage to the hydrogen fuel tank, but also easily leads to the destruction of the overall structure of the unmanned aerial vehicle, thereby causing equipment losses and even threatening personal safety. Summary of the Invention

[0004] In view of the above problems, a hydrogen fuel protection device for a hydrogen fuel cell used in an unmanned aerial vehicle is provided. By proposing a device that can not only monitor the hydrogen fuel cell in real time but also comprehensively and effectively protect the hydrogen fuel cell, the technical problems that existing protection devices are usually large in volume and complex in structure; they cannot effectively protect against hydrogen leakage and the leaked hydrogen easily affects flight performance are solved.

[0005] To solve the problems of the existing technology, the present invention provides a hydrogen fuel protection device for a hydrogen fuel cell of an unmanned aerial vehicle, comprising: an unmanned aerial vehicle, a hydrogen fuel tank and a hydrogen fuel cell provided on the unmanned aerial vehicle; an upper protection module, the hydrogen fuel tank is detachably provided on the top of the unmanned aerial vehicle through the upper protection module; the upper protection module is provided with a protective cover for protecting the hydrogen fuel tank in real time and an active protection unit for actively separating the protective cover from the unmanned aerial vehicle in a protected state; the upper protection module further includes a guiding unit for guiding the hydrogen leaked from the hydrogen fuel tank in a specific direction; a lower protection module, the hydrogen fuel cell is detachably provided below the unmanned aerial vehicle through the lower protection module; the lower protection module is provided with a buffer rack for comprehensively protecting the hydrogen fuel cell in a protected state; the lower protection module further includes a guiding rack for longitudinally guiding the sliding of the buffer rack and an opening and closing unit for driving the buffer rack to buffer.

[0006] Preferably, the guiding unit is vertically arranged outside the protective cover and a plurality of groups are circumferentially arranged along the axis of the protective cover.

[0007] Preferably, the guiding unit is provided with a first outlet nozzle and a second outlet nozzle for leading hydrogen out of the protective cover; the first outlet nozzle is vertically arranged at the top of the protective cover and communicated with the inside of the protective cover; a plurality of first outlet nozzles are equidistantly arranged along the long side direction of the protective cover; the second outlet nozzles are provided in two groups, and the two groups of second outlet nozzles are relatively vertically arranged on both sides of the protective cover and communicated with the inside of the protective cover; a plurality of the two groups of second outlet nozzles are equidistantly arranged along the long side direction of the protective cover.

[0008] Preferably, the guiding unit further includes a first one-way valve and a second one-way valve that are opened under a first pressure and a second pressure; the first one-way valve and the second one-way valve are respectively coaxially fixed in the first outlet nozzle and the second outlet nozzle.

[0009] Preferably, the active protection unit is provided with a locking unit for locking between the protective cover and the unmanned aerial vehicle in a non-protected state and an unlocking unit for actively driving the locking unit to unlock in a protected state.

[0010] Preferably, the active protection unit also includes a guide rod, a first spring, a second spring and an air duct; the guide rod is vertically fixed on the top of the drone, the guide rod is a hollow rod body that passes through the top and bottom, and the top of the guide rod is also radially penetrated by a through hole; the first spring is coaxially arranged in the guide rod; the locking unit is coaxially slidably arranged in the guide rod and the bottom abuts against the top of the first spring; the locking end of the locking unit passes through the through hole and is arranged toward the outside of the guide rod; the second spring is coaxially sleeved and installed outside the guide rod; the air duct is coaxially arranged on the top of the guide rod, one end of the air duct is connected to the guide rod, and the other end is connected to the guiding end of the guide unit; the unlocking unit is fixedly arranged in the drone and the unlocking end is connected to the bottom of the locking unit.

[0011] Preferably, the locking unit includes a sliding rod, a sealing plug, an elastic locking rod and a guide seat; the sealing plug is coaxially fixed on the top of the sliding rod; two elastic locking rods are provided, and the two elastic locking rods are relatively fixed in an inclined state on both sides of the sliding rod; the guide seat is coaxially fixed on the bottom of the sliding rod.

[0012] Preferably, the guide frame is vertically fixed on the bottom of the drone; the hydrogen fuel cell is fixedly arranged in the guide frame; the buffer frame is vertically slidably arranged outside the guide frame and multiple buffer frames are circumferentially arranged along the axis of the guide frame; the opening and closing unit is embedded in the guide frame.

[0013] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention realizes directional one-way hydrogen discharge when a small amount of hydrogen leakage occurs by arranging a first outlet nozzle at the top of the protective cover and a first one-way valve coaxially arranged in the first outlet nozzle, so that the leaked hydrogen only produces controllable longitudinal downforce on the UAV, avoiding flight attitude imbalance caused by lateral thrust. Furthermore, through two second outlet nozzles and the second one-way valves arranged therein, hydrogen is evenly discharged in an annular direction in the event of a large-scale leakage, and the leakage pressure is dispersed in a coordinated manner, which significantly improves flight stability and safety.

[0014] 2. The present invention realizes the ejection and separation of the protective cover and the hydrogen fuel tank by setting an active protection unit that can be unlocked actively and passively, and actively realizes the rapid physical isolation of the UAV and the hydrogen fuel tank. At the same time, the high pressure generated by the leaked hydrogen in the protective cover can automatically trigger the passive unlocking mechanism, and the hydrogen is applied to the sliding rod through the air guide to cause the locking unit to slide longitudinally, thereby realizing the unlocking action and meeting the emergency protection needs when manual control is not possible.

[0015] 3. The present invention can provide a multi-stage pressure relief and export mechanism and a staged structural isolation protection at different stages of the hydrogen fuel tank from a trace amount to a large amount of leakage, realizing the continuous and safe operation of the UAV system in a complex environment, and effectively reducing the equipment damage and personnel safety risks caused by hydrogen fuel leakage. Brief Description of the Drawings

[0016] Figure 1 is a perspective view of a hydrogen fuel protection device for a hydrogen fuel cell of a UAV.

[0017] Figure 2 is a side view of a hydrogen fuel protection device for a hydrogen fuel cell of a UAV. Figure 1 .

[0018] Figure 3 is Figure 2 a sectional view taken along the line A-A of

[0019] Figure 4 is Figure 3 a partially enlarged view at B of

[0020] Figure 5 is a side view of a hydrogen fuel protection device for a hydrogen fuel cell of a UAV. Figure 2 .

[0021] Figure 6 is a side view of a hydrogen fuel protection device for a hydrogen fuel cell of a UAV with the lower protection module and the hydrogen fuel cell removed.

[0022] Figure 7 is Figure 6 a sectional view taken along the line C-C of

[0023] Figure 8 is an exploded perspective view of the hydrogen fuel cell and the lower protection module of a hydrogen fuel protection device for a hydrogen fuel cell of a UAV.

[0024] Figure 9 is an exploded perspective view of a partial structure of the hydrogen fuel tank and the upper protection module of a hydrogen fuel protection device for a hydrogen fuel cell of a UAV.

[0025] Figure 10 is an exploded perspective view of a partial structure of the upper protection module of a hydrogen fuel protection device for a hydrogen fuel cell of a UAV.

[0026] The reference numerals in the drawings are:

[0027] 1. UAV; 11. Hydrogen fuel tank; 12. Hydrogen fuel cell;

[0028] 2. Upper protection module; 21. Protective cover; 211. Buffer airbag; 22. Active protection unit; 221. Locking unit; 2211. Sliding rod; 2212. Sealing plug; 2213. Elastic locking rod; 2214. Guide seat; 222. Unlocking unit; 2221. Pull rope; 2222. Retractor; 223. Guide rod; 2231. Through hole; 224. First spring; 225. Second spring; 226. Air guide tube; 23. Guide unit; 231. First outlet nozzle; 232. Second outlet nozzle; 233. First one-way valve; 234. Second one-way valve;

[0029] 3. Lower protection module; 31. Buffer frame; 32. Guide frame; 33. Opening and closing unit; 34. Third spring. DETAILED DESCRIPTION

[0030] In order to further understand the features, technical means, specific objectives and functions of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0031] See also Figures 1 to 10 As shown: A hydrogen fuel protection device for a hydrogen fuel cell for an unmanned aerial vehicle, comprising: an unmanned aerial vehicle 1, a hydrogen fuel tank 11 and a hydrogen fuel cell 12 arranged on the unmanned aerial vehicle 1; an upper protection module 2, wherein the hydrogen fuel tank 11 is detachably arranged on the top of the unmanned aerial vehicle 1 through the upper protection module 2; the upper protection module 2 is provided with a protective cover 21 for real-time protection of the hydrogen fuel tank 11 and an active protection unit 22 for actively separating the protective cover 21 from the unmanned aerial vehicle 1 in a protection state; the upper protection module 2 also includes a guiding unit 23 for directional guidance of hydrogen leaked from the hydrogen fuel tank 11; a lower protection module 3, wherein the hydrogen fuel cell 12 is detachably arranged under the unmanned aerial vehicle 1 through the lower protection module 3; the lower protection module 3 is provided with a buffer frame 31 for comprehensively protecting the hydrogen fuel cell 12 in a protection state; the lower protection module 3 also includes a guiding frame 32 for longitudinally guiding the sliding of the buffer frame 31 and an opening and closing unit 33 for driving the buffer frame 31 for buffering.

[0032] During the flight of the drone 1, if an abnormal situation occurs, especially when the hydrogen fuel tank 11 leaks, in order to avoid disordered flight posture or even safety accidents caused by the disordered diffusion of the leaked gas, the upper protection module 2 first enters the working state. The upper protection module 2 can automatically adjust the opening mode of the guide unit 23 according to the direction and flow rate characteristics of the leaked hydrogen, ensuring that the leaked hydrogen is guided out of the protective cover 21 along the set channel in a stable and controllable path, which can not only effectively inhibit the turbulent diffusion of hydrogen, but also reduce the disturbance to the flight posture of the drone 1, thereby avoiding the problem of imbalance in the flight posture of the drone 1 caused by leakage.

[0033] Further, when it is detected that the hydrogen fuel tank 11 has a severe leak and is likely to cause serious impacts on the main structure of the UAV 1 and its flight control system, the active protection unit 22 is immediately activated. The protective cover 21 detachably arranged on the UAV 1 is quickly separated from the main body of the UAV 1 along a preset ejection path, so as to realize the physical separation of the hydrogen fuel tank 11 from the UAV 1 system and effectively cut off the potential fuel source risk.

[0034] At the same time when the active protection unit 22 is activated, the lower protection module 3 is also automatically linked and deployed. The buffer frame 31 structure in the lower protection module 3 can form an all-round wrapped buffer protection for the hydrogen fuel cell 12 after deployment. On the one hand, it reduces the mechanical impact on the fuel cell during the separation process, and on the other hand, it prevents the hydrogen fuel cell 12 from being damaged due to direct impact in the case where the UAV 1 may fall, thereby significantly improving the overall safety and stability of the system.

[0035] Through the provided upper protection module 2, an effective guidance for the hydrogen leakage path can be realized, the controllability of leakage control can be improved, and the flight balance of the UAV 1 can be ensured; further, through the ejection separation mechanism of the active protection unit 22 and the linked buffer protection device of the lower protection module 3, when the hydrogen fuel tank 11 has a severe leak, active safety isolation and protection measures can be quickly implemented, significantly reducing the damage risk of hydrogen fuel leakage to the UAV 1 and the hydrogen fuel cell 12 system, thereby improving the safety level and reliability of the UAV 1 in a high-risk application environment.

[0036] See Figure 3 As shown: The guiding unit 23 is vertically arranged outside the protective cover 21 and multiple groups are circumferentially arranged along the axis of the protective cover 21.

[0037] When the hydrogen fuel tank 11 leaks during use, in order to ensure that the leaked hydrogen does not affect the flight trajectory of the UAV 1 in the normal flight state; when the hydrogen fuel tank 11 fixedly arranged in the protective cover 21 leaks, through the guidance of the guiding unit 23, the leaked hydrogen can be effectively and evenly guided in a specific direction, so as to realize that even if the hydrogen fuel tank 11 leaks, the leaked hydrogen can be effectively guided to be exported in the correct posture, so that while not affecting the correct flight of the UAV 1, the leaked hydrogen can also be used to make a correct guidance for the UAV 1.

[0038] See Figure 9As shown in the figure: The guiding unit 23 is provided with a first outlet nozzle 231 and a second outlet nozzle 232 for discharging hydrogen from within the protective cover 21; the first outlet nozzle 231 is vertically disposed at the top of the protective cover 21 and is in communication with the interior of the protective cover 21; a plurality of the first outlet nozzles 231 are equidistantly arranged along the long side direction of the protective cover 21; there are two groups of the second outlet nozzles 232, and the two groups of second outlet nozzles 232 are oppositely and vertically disposed on both sides of the protective cover 21 and are in communication with the interior of the protective cover 21; a plurality of the two groups of second outlet nozzles 232 are equidistantly arranged along the long side direction of the protective cover 21.

[0039] The protective cover 21 is a hollow polygonal shell with an open bottom, and a buffer airbag 211 is fixedly provided at each corner of the polygonal shell.

[0040] Through the structure of the first outlet nozzle 231 opened at the top of the protective cover 21, when a small-scale leakage occurs in the hydrogen fuel tank 11, it can play a function of directionally discharging the leaked hydrogen. The outlet direction of the first outlet nozzle 231 is precisely defined, so that the leaked hydrogen gas flow is always discharged vertically downward along a direction perpendicular to the body of the unmanned aerial vehicle 1, thereby only generating a stable and controllable downward pressure on the unmanned aerial vehicle 1 longitudinally, avoiding the generation of lateral thrust or rotational disturbance on the unmanned aerial vehicle 1 due to the uncertain flow direction of the leaked gas, and ensuring the stability and safety of the flight attitude.

[0041] Furthermore, to address the problem of a large amount of hydrogen leakage generated by the hydrogen fuel tank 11 under high pressure or structural damage conditions, the present invention circumferentially arranges two second outlet nozzles 232 on the side wall of the protective cover 21. The second outlet nozzles 232 are evenly distributed in a symmetric manner and can work together in the case of large-flow leakage to respectively unidirectionally guide the hydrogen leakage flow, so that the leaked gas is evenly discharged along the outer periphery in a circumferential distribution state. This structure can effectively reduce the asymmetric impact formed by high-pressure hydrogen at the initial stage of leakage and avoid the uneven force on the unmanned aerial vehicle 1 caused by uneven local pressure relief, thereby ensuring the stable operation of the system under extreme working conditions.

[0042] The directional discharge of trace leaked hydrogen is achieved through the first outlet nozzle 231, avoiding the influence of lateral disturbance on the flight attitude; a circumferentially evenly distributed pressure relief path is constructed through the second outlet nozzle 232 to ensure the uniformity and controllability of pressure release when dealing with a large amount of leakage, thereby effectively improving the safety control ability and flight stability of the unmanned aerial vehicle 1 under hydrogen leakage conditions.

[0043] See Figure 4 and Figure 9As shown: The guiding unit 23 further includes a first one-way valve 233 and a second one-way valve 234 that are opened under a first pressure and a second pressure; the first one-way valve 233 and the second one-way valve 234 are coaxially and fixedly arranged in the first outlet nozzle 231 and the second outlet nozzle 232 respectively.

[0044] The first one-way valve 233 is set to open under a first preset pressure, and the second one-way valve 234 is set to open under a second preset pressure higher than the first preset pressure. Thus, it can be realized that according to different levels of the hydrogen pressure in the protective cover 21 when the hydrogen fuel tank 11 leaks, the corresponding export channels can be automatically selected to open: when the leakage amount is small, the hydrogen pressure in the protective cover 21 is lower than the first preset value, the first one-way valve 233 remains closed, and the system remains sealed; when the leakage amount reaches the first pressure threshold, the first one-way valve 233 automatically opens, guiding hydrogen to be preferentially discharged through the first outlet nozzle 231 in a directional manner; when the leakage amount continues to increase, resulting in the pressure exceeding the second pressure threshold, the second one-way valve 234 synchronously opens, and hydrogen is then evenly discharged through the second outlet nozzles 232 distributed circumferentially around the protective cover 21 in a circumferential and multi-point manner.

[0045] Through this hierarchical pressure relief control mechanism, the intelligent management of the hydrogen discharge path under different leakage levels is realized, ensuring that rapid, safe, and directional gas export can be achieved under any leakage intensity, effectively avoiding the risk of the disordered leakage of hydrogen disturbing the flight attitude of the drone 1.

[0046] By setting the first one-way valve 233 and the second one-way valve 234 with different opening pressures, the hydrogen can be automatically shunted and discharged according to the pressure when leaking, which can not only realize the directional export of small amounts of leakage but also cope with the circumferential uniform pressure discharge of large amounts of leakage, thereby improving the flight stability and safety guarantee ability of the drone 1 during the hydrogen fuel leakage process.

[0047] See Figure 4 As shown: The active protection unit 22 is provided with a locking unit 221 for locking between the protective cover 21 and the drone 1 in a non-protective state and an unlocking unit 222 for actively driving the locking unit 221 to unlock in a protective state.

[0048] When the hydrogen fuel tank 11 has a severe leak during flight and the leakage condition has reached a critical state that affects the flight stability or safe operation of the drone 1, it is necessary to quickly achieve the active throwing away of the hydrogen fuel tank 11 to prevent the accident from expanding. At this time, by driving the unlocking unit 222 to control the action of the locking unit 221, the protective cover 21 can be detached from the drone 1 to achieve the purpose of throwing away the protective cover 21 and the hydrogen fuel tank 11 arranged in the protective cover 21.

[0049] Since the hydrogen fuel tank 11 is designed to be integrally installed inside the protective cover 21, when the protective cover 21 is ejected and separated, it will carry the hydrogen fuel tank 11 away from the UAV 1 body together, thus realizing the rapid separation between the hydrogen fuel tank 11 and the UAV 1. This process does not rely on external manual intervention, can complete the physical isolation of the fuel source in a very short time, reduce the risk of continuous spread of hydrogen leakage, and effectively prevent safety accidents such as secondary flight out of control or deflagration of the UAV 1 caused by abnormal fuel systems.

[0050] See Figure 4 As shown in the figure: The active protection unit 22 further includes a guide rod 223, a first spring 224, a second spring 225, and an air duct 226; the guide rod 223 is vertically and fixedly arranged on the top of the UAV 1, the guide rod 223 is a hollow rod body that penetrates up and down, and a through hole 2231 is radially penetrated through the top of the guide rod 223; the first spring 224 is coaxially arranged inside the guide rod 223; the locking unit 221 is coaxially and slidably arranged inside the guide rod 223 and the bottom abuts against the top of the first spring 224; the locking end of the locking unit 221 passes through the through hole 2231 and is arranged towards the outside of the guide rod 223; the second spring 225 is coaxially sleeved and installed outside the guide rod 223; the air duct 226 is coaxially arranged on the top of the guide rod 223, one end of the air duct 226 communicates with the guide rod 223, and the other end communicates with the guiding end of the guiding unit 23; the unlocking unit 222 is fixedly arranged inside the UAV 1 and the unlocking end is connected to the bottom of the locking unit 221.

[0051] In the installed state, the protective cover 21 is longitudinally limited by the guide rod 223, stably arranged on the UAV 1 frame, and the locking unit 221 is used to limit and fix the connection between it and the guide rod 223, so as to realize the reliable fixation of the protective cover 21 during flight. Specifically, the locking end of the locking unit 221 extends into the through hole 2231 arranged on the guide rod 223 by means of insertion and clamping to form a stable limiting and fixing connection; at the same time, the second spring 225 arranged outside the guide rod 223 will be in a continuously compressed state and always apply an upward supporting force to the protective cover 21, so that the protective cover 21 is kept in close contact with the locking end of the locking unit 221, enhancing the fixing effect.

[0052] The unlocking unit 222 is specifically composed of a pull rope 2221 and a reel 2222; one end of the pull rope 2221 is fixedly connected to the bottom of the locking unit 221, and the other end is connected to the winding end of the reel 2222.

[0053] When it is necessary to actively separate the protective cover 21 from the guide rod 223, the unlocking unit 222 is driven to act. At this time, the winding end of the retractor 2222 performs an action to wind the pulling rope 2221, so as to continuously pull the locking unit 221 to move longitudinally downward in the guide rod 223 until the locking end of the locking unit 221 completely retracts from the through hole 2231 into the guide rod 223, thus realizing the active unlocking of the protective cover 21, and further releasing the limited connection between the protective cover 21 and the guide rod 223.

[0054] In addition, to further improve the safety response ability of the system under sudden leakage conditions, the guide rod 223 is communicated with the second outlet nozzle 232 arranged at the middle upper part of the protective cover 21 through an air duct 226 to form a pressure relief guiding channel. When a large air pressure is generated inside the protective cover 21 due to the leakage of the hydrogen fuel tank 11, this air pressure is transmitted to the lower part of the unlocking unit 222 through the air duct 226. When the pressure reaches the set threshold value, the leaked hydrogen can push the unlocking unit 222 to move longitudinally downward without external control, overcoming the elastic limit of the first spring 224, and completing the passive release operation of the locking end, thereby realizing the automatic unlocking and rapid detachment of the protective cover 21 under passive control conditions, and ensuring the safety isolation response of the drone 1 in case of emergency leakage.

[0055] See Figure 7 and Figure 10 As shown: The locking unit 221 includes a sliding rod 2211, a sealing plug 2212, an elastic locking rod 2213 and a guide seat 2214; the sealing plug 2212 is coaxially and fixedly arranged at the top of the sliding rod 2211; there are two elastic locking rods 2213, and the two elastic locking rods 2213 are relatively fixedly arranged on both sides of the sliding rod 2211 in an inclined state; the guide seat 2214 is coaxially and fixedly arranged at the bottom of the sliding rod 2211.

[0056] In the locked state, the front ends of the two elastic locking rods 2213 are both arranged to pass through the through hole 2231 in an inclined state, so as to realize the locking effect between the guide rod 223 and the protective cover 21; and because the two elastic locking rods 2213 are both fixedly arranged on both sides of the sliding rod 2211 in an inclined state, when the sliding rod 2211 is subjected to a longitudinal thrust, it will cooperate with the two elastic locking rods 2213 to incline and contract towards the inside of the sliding rod 2211, thus realizing the unlocking effect between the protective cover 21 and the guide rod 223; the sealing plug 2212 and the inner wall of the guide rod 223 are in clearance fit, so as to realize a good pushing effect when using the hydrogen leaked inside the protective cover 21 to push the sliding rod 2211; the guide seat 2214 is used to axially guide the sliding rod 2211 to slide in the guide rod 223.

[0057] See Figure 8 As shown: The guiding frame 32 is vertically and fixedly arranged at the bottom of the UAV 1; The hydrogen fuel cell 12 is fixedly arranged in the guiding frame 32; The buffer frame 31 is vertically slidably arranged outside the guiding frame 32 and a plurality of buffer frames 31 are circumferentially arranged along the axis of the guiding frame 32; The opening and closing unit 33 is embedded in the guiding frame 32.

[0058] The lower protection module 3 further includes a third spring 34 arranged between the guiding frame 32 and the buffer frame 31. The third spring 34 is used to provide an elastic supporting force in the vertical direction. One end of the third spring 34 is fixedly connected to the bottom of the guiding frame 32, and the other end is fixedly connected to the top of the buffer frame 31, thereby constructing a stable elastic buffer support structure. The third spring 34 is in an energy storage deformation state in the compressed state and can provide a longitudinal elastic force when released to drive the movement of the buffer frame 31.

[0059] The opening and closing unit 33 is preferably an electromagnet structure. The electromagnet is fixedly installed outside the guiding frame 32 in an embedded manner and is arranged near the top of the guiding frame 32, which is convenient for controlling the magnetic adsorption and release of the buffer frame 31. In the non-buffering working state, the buffer frame 31 is adsorbed and compressed by the magnetic force of the electromagnet and positioned on the side wall of the guiding frame 32, so as to keep the structure compact and the system stable.

[0060] When it is detected that there is a potential impact threat to the hydrogen fuel cell 12, or when the buffer protection mechanism needs to be activated, the opening and closing unit 33 can be driven to release the adsorption by controlling the on-off state of the electromagnet. At this time, the third spring 34 in the compressed state quickly releases the stored energy elastic force, pushing the buffer frame 31 to move downward along the axial direction of the guiding frame 32, so as to form an effective buffer gap between the buffer frame 31 and the guiding frame 32. At the same time, the buffer frame 31 is longitudinally extended under the driving of the elastic restoring force of the third spring 34, thereby forming a dynamic elastic buffer structure, which can absorb and conduct the impact energy to the greatest extent when encountering external impact loads and significantly relieve the mechanical impact on the hydrogen fuel cell 12.

[0061] The present invention can not only detect the hydrogen fuel tank in real time but also provide comprehensive protection for it.

[0062] The above embodiments only represent one or several implementation manners of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.

Claims

1. A hydrogen fuel protection device for a hydrogen fuel cell used in a drone, characterized in that, Comprising: A drone, a hydrogen fuel tank and a hydrogen fuel cell provided on the drone; An upper protection module, the hydrogen fuel tank is detachably provided on the top of the drone through the upper protection module; The upper protection module is provided with a protective cover for protecting the hydrogen fuel tank in real time and an active protection unit for actively disengaging the protective cover from the drone in the protection state; the upper protection module further includes a guiding unit for guiding the leaked hydrogen from the hydrogen fuel tank in a specific direction; A lower protection module, the hydrogen fuel cell is detachably provided below the drone through the lower protection module; the lower protection module is provided with a buffer rack for comprehensively protecting the hydrogen fuel cell in the protection state; the lower protection module further includes a guiding rack for longitudinally guiding the sliding of the buffer rack and an opening and closing unit for driving the buffer rack to buffer; 2. The hydrogen fuel protection device for a hydrogen fuel cell used in a drone according to claim 1, characterized in that, The guiding unit is vertically arranged outside the protective cover and a plurality of groups are circumferentially arranged along the axis of the protective cover.

3. The hydrogen fuel protection device for a hydrogen fuel cell used in a drone according to claim 2, characterized in that, The guiding unit is provided with a first outlet nozzle and a second outlet nozzle for guiding hydrogen out of the protective cover; The first outlet nozzle is vertically arranged on the top of the protective cover and is communicated with the inside of the protective cover; a plurality of first outlet nozzles are equidistantly arranged along the long side direction of the protective cover; The second outlet nozzle is provided with two groups, and the two groups of second outlet nozzles are relatively vertically arranged on both sides of the protective cover and are communicated with the inside of the protective cover; a plurality of the two groups of second outlet nozzles are equidistantly arranged along the long side direction of the protective cover.

4. The hydrogen fuel protection device for a hydrogen fuel cell used in a drone according to claim 3, characterized in that, The guiding unit further includes a first one-way valve and a second one-way valve for opening under a first pressure and a second pressure; The first one-way valve and the second one-way valve are respectively coaxially and fixedly arranged in the first outlet nozzle and the second outlet nozzle.

5. The hydrogen fuel protection device for a hydrogen fuel cell used in a drone according to claim 1, characterized in that, The active protection unit is provided with a locking unit for locking between the protective cover and the drone in the non-protection state and an unlocking unit for actively driving the locking unit to unlock in the protection state.

6. The hydrogen fuel protection device for a hydrogen fuel cell used in a drone according to claim 5, characterized in that, The active protection unit further includes a guiding rod, a first spring, a second spring and an air guide pipe; The guiding rod is vertically and fixedly arranged on the top of the drone, the guiding rod is a hollow rod body that penetrates up and down, and a through hole is radially opened at the top of the guiding rod; The first spring is coaxially arranged in the guiding rod; The locking unit is coaxially slidably arranged in the guiding rod and the bottom abuts against the top of the first spring; the locking end of the locking unit passes through the through hole and is arranged towards the outside of the guiding rod; The second spring is coaxially sleeved and installed outside the guiding rod; The air guide pipe is coaxially arranged on the top of the guiding rod, one end of the air guide pipe is communicated with the guiding rod, and the other end is communicated with the guiding end of the guiding unit; The unlocking unit is fixedly arranged in the drone and the unlocking end is connected to the bottom of the locking unit.

7. The hydrogen fuel protection device for a hydrogen fuel cell used in a drone according to claim 5, characterized in that, The locking unit includes a sliding rod, a sealing plug, an elastic locking rod and a guiding seat; The sealing plug is coaxially and fixedly arranged on the top of the sliding rod; There are two elastic locking rods, and the two elastic locking rods are relatively fixedly arranged on both sides of the sliding rod in an inclined state; The guiding seat is coaxially and fixedly arranged on the bottom of the sliding rod.

8. The hydrogen fuel protection device for a hydrogen fuel cell used in a drone according to claim 1, characterized in that, The guiding frame is vertically and fixedly arranged at the bottom of the drone; The hydrogen fuel cell is fixedly arranged in the guiding frame; The buffer frame is vertically and slidably arranged outside the guiding frame, and a plurality of buffer frames are circumferentially arranged along the axis of the guiding frame; The opening and closing unit is embedded and installed in the guiding frame.

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