A hydrogen fuel protection device for a hydrogen fuel cell used in a drone

Abstract

The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a hydrogen fuel protection device for a hydrogen fuel cell for a UAV, comprising: a UAV, a hydrogen fuel tank and a hydrogen fuel cell arranged on the UAV; an upper protection module, through which the hydrogen fuel tank is detachably arranged on the top of the UAV; the upper protection module is provided with a protective cover for real-time protection of the hydrogen fuel tank and an active protection unit for actively separating the protective cover from the UAV in a protective state; a lower protection module, through which the hydrogen fuel cell is detachably arranged below the UAV; the lower protection module is provided with a buffer rack for fully protecting the hydrogen fuel cell in a protective state; the present invention can not only perform real-time detection on the hydrogen fuel tank but also provide comprehensive protection for it.

Description

Technical Field

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

[0002] Amid the continued development of drone technology, hydrogen fuel cells are gradually becoming a power system option for the new generation of drones due to their high energy density and clean emissions. However, as a high-pressure, highly flammable gas energy source, hydrogen fuel carries a high risk of leakage during actual use. This is especially true during drone flight. Leaks in hydrogen fuel tanks due to high-pressure system leaks, leaks at interfaces, or mechanical vibrations can not only waste fuel but also pose serious structural safety risks. In particular, when a leak occurs on any side of the fuel tank, the leaked hydrogen will eject at high speed from the leak point. Due to the uneven direction of the force, it will generate asymmetric thrust on the drone, causing problems such as flight yaw and attitude instability, seriously affecting the drone's flight control and operational accuracy.

[0003] In addition, since hydrogen has an extremely high explosion limit range and extremely low ignition energy, when the leakage concentration accumulates to the critical explosion range, it is very easy to cause a combustion and explosion accident if it encounters a fire source or electric spark. It may not only cause damage to the hydrogen fuel tank, but also easily cause damage to the overall structure of the drone, thereby causing equipment loss and even threatening personnel safety. Summary of the Invention

[0004] In response to the above problems, a hydrogen fuel protection device for hydrogen fuel cells used in drones is provided. By proposing a device that can not only monitor the hydrogen fuel cell in real time but also provide comprehensive and effective protection for the hydrogen fuel cell, the technical problems that existing protection devices are usually large in size and complex in structure, cannot effectively protect the hydrogen when it leaks, and the leaked hydrogen is likely to affect the flight performance are solved.

[0005] In order to solve the problems of the prior art, the present invention provides a hydrogen fuel protection device for a hydrogen fuel cell for an unmanned aerial vehicle, comprising: a unmanned aerial vehicle, a hydrogen fuel tank and a hydrogen fuel cell arranged on the unmanned aerial vehicle; an upper protection module, through which the hydrogen fuel tank is detachably arranged on the top of the unmanned aerial vehicle; the upper protection module is provided with a protective cover for real-time protection of the hydrogen fuel tank and an active protection unit for actively separating the protective cover from the unmanned aerial vehicle in a protection state; the upper protection module also includes a guiding unit for directionally guiding the hydrogen leaked from the hydrogen fuel tank; a lower protection module, through which the hydrogen fuel cell is detachably arranged under the unmanned aerial vehicle; the lower protection module is provided with a buffer rack for comprehensively protecting the hydrogen fuel cell in a protection state; the lower protection module also includes a guide rack for longitudinally guiding the sliding of the buffer rack and an opening and closing unit for driving the buffer rack to perform buffering.

[0006] Preferably, the guide units are vertically arranged outside the protective cover and are arranged in multiple groups circumferentially along the axis of the protective cover.

[0007] Preferably, the guide unit is provided with a first outlet nozzle and a second outlet nozzle for outlet hydrogen from the protective cover; the first outlet nozzle is vertically arranged at the top of the protective cover and is connected to the interior of the protective cover; a plurality of the first outlet nozzles are equidistantly arranged along the long side direction of the protective cover; two groups of the second outlet nozzles are provided, and the two groups of the second outlet nozzles are relatively vertically arranged on both sides of the protective cover and are connected to the interior of the protective cover; a plurality of the two groups of the second outlet nozzles are equidistantly arranged along the long side direction of the protective cover.

[0008] Preferably, the guide unit further comprises a first one-way valve and a second one-way valve for opening under the first pressure and the second pressure; the first one-way valve and the second one-way valve are coaxially fixedly arranged in the first outlet nozzle and the second outlet nozzle respectively.

[0009] Preferably, the active protection unit is provided with a locking unit for locking the protective cover and the drone in a non-protective state and an unlocking unit for actively driving the locking unit to unlock in a protective 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 is penetrated up and down, and the top of the guide rod is also radially penetrated with 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 at 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 guide 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 fixed inside 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:

[0014] 1. This invention utilizes a first discharge nozzle located at the top of the protective cover and a first one-way valve coaxially positioned within the first discharge nozzle to achieve directional, one-way discharge of hydrogen in the event of a small leak. This ensures that the leaked hydrogen exerts only a controllable longitudinal downforce on the drone, preventing lateral thrust from causing flight imbalance. Furthermore, two second discharge nozzles and the second one-way valves within them ensure uniform circumferential discharge of hydrogen in the event of a large-scale leak, synergistically dispersing the leak pressure and significantly improving flight stability and safety.

[0015] 2. By incorporating an active protection unit capable of both active and passive unlocking, this invention achieves ejection separation between the protective cover and the hydrogen fuel tank, proactively and rapidly physically isolating the drone from the hydrogen fuel tank. Furthermore, the high pressure generated by hydrogen leaking from the protective cover automatically triggers the passive unlocking mechanism. Hydrogen is then applied to the sliding rod via an air duct, causing the locking unit to slide longitudinally, achieving unlocking. This meets emergency protection needs when manual control is unavailable.

[0016] 3. The present invention can provide a multi-stage pressure relief mechanism and phased structural isolation protection at different stages of hydrogen fuel tank leakage, ranging from trace to large amounts, to achieve continuous and safe operation of the UAV system in complex environments, effectively reducing equipment damage and personnel safety risks caused by hydrogen fuel leakage. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a three-dimensional diagram of a hydrogen fuel protection device for a hydrogen fuel cell used in an unmanned aerial vehicle.

[0018] Figure 2 A side view of a hydrogen fuel protection device for a hydrogen fuel cell used in a drone Figure 1 .

[0019] Figure 3 yes Figure 2 Cross-sectional view at AA.

[0020] Figure 4 yes Figure 3 A partial enlarged view of point B.

[0021] Figure 5 A side view of a hydrogen fuel protection device for a hydrogen fuel cell used in a drone Figure 2 .

[0022] Figure 6 The figure is a side view of a hydrogen fuel protection device for a hydrogen fuel cell for an unmanned aerial vehicle, with the lower protection module and the hydrogen fuel cell removed.

[0023] Figure 7 yes Figure 6 Cross-sectional view at CC.

[0024] Figure 8 This is an exploded perspective view of the hydrogen fuel cell and lower protection module in a hydrogen fuel protection device for a hydrogen fuel cell used in a drone.

[0025] Figure 9 This is a three-dimensional exploded view of the hydrogen fuel tank and upper protection module structure of a hydrogen fuel protection device for a hydrogen fuel cell used in a drone.

[0026] Figure 10 This is a three-dimensional exploded view of the structure of the upper protection module of a hydrogen fuel protection device for a hydrogen fuel cell used in a drone.

[0027] The numbers in the figure are:

[0028] 1. UAV; 11. Hydrogen fuel tank; 12. Hydrogen fuel cell;

[0029] 2. Upper protection module; 21. Protective cover; 211. Cushioning 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;

[0030] 3. Lower protection module; 31. Buffer frame; 32. Guide frame; 33. Opening and closing unit; 34. Third spring. DETAILED DESCRIPTION

[0031] In order to further understand the features, technical means, specific objectives and functions achieved by the present invention, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0032] See also Figures 1 to 10 As shown: A hydrogen fuel protection device for a hydrogen fuel cell for an unmanned aerial vehicle, comprising: a 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 guide unit 23 for directionally guiding the 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 guide 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.

[0033] If an abnormal situation occurs during the flight of the drone 1, especially a leak in the hydrogen fuel tank 11, the upper protection module 2 first enters operation to prevent flight attitude disturbances or even safety accidents caused by the disordered diffusion of the leaked gas. The upper protection module 2 automatically adjusts the opening mode of the guide unit 23 based on the direction and flow rate characteristics of the leaking hydrogen, ensuring that the leaked hydrogen is guided out of the protective cover 21 along a predetermined path in a stable and controllable manner. This not only effectively suppresses the turbulent diffusion of hydrogen, but also reduces disturbances to the flight attitude of the drone 1, thereby preventing flight attitude imbalances caused by leaks.

[0034] Furthermore, if a severe leak from the hydrogen fuel tank 11 is detected, potentially causing serious damage to the main structure of the drone 1 and its flight control system, the active protection unit 22 is activated. This causes the detachable protective cover 21 on the drone 1 to quickly detach from the drone 1 along a pre-set ejection path, thereby physically separating the hydrogen fuel tank 11 from the drone 1 system and effectively cutting off potential fuel source risks.

[0035] When the active protection unit 22 is activated, the lower protection module 3 is automatically deployed. The buffer frame 31 in the lower protection module 3, when deployed, provides a fully enveloping buffer for the hydrogen fuel cell 12. This not only reduces mechanical shock to the fuel cell during the detachment process, but also prevents damage to the hydrogen fuel cell 12 from direct impact in the event of a potential fall of the drone 1, significantly improving the overall safety and stability of the system.

[0036] Through the upper protection module 2, the hydrogen leakage path can be effectively guided, the controllability of leakage control can be improved, and the flight balance of the drone 1 can be guaranteed; further, through the ejection separation mechanism of the active protection unit 22 and the linkage buffer protection device of the lower protection module 3, active safety isolation and protection measures can be quickly implemented when a serious leak occurs in the hydrogen fuel tank 11, which significantly reduces the risk of damage to the drone 1 and the hydrogen fuel cell 12 system caused by hydrogen fuel leakage, thereby improving the safety level and reliability of the drone 1 in high-risk application environments.

[0037] See also Figure 3 As shown, the guide units 23 are vertically arranged outside the protective cover 21 and multiple groups are arranged circumferentially along the axis of the protective cover 21.

[0038] When the hydrogen fuel tank 11 leaks while in use, in order to ensure that the leaked hydrogen does not affect the flight trajectory of the drone 1 in a normal flight state; when the hydrogen fuel tank 11 fixedly arranged in the protective cover 21 leaks, the guidance of the guiding unit 23 can achieve effective and uniform directional guidance of the leaked hydrogen, so that even if the hydrogen fuel tank 11 leaks, the leaked hydrogen can be effectively guided to be discharged in the correct posture, so that the leaked hydrogen can be used to correctly guide the drone 1 without affecting the correct flight of the drone 1.

[0039] See also Figure 9As shown: the guide unit 23 is provided with a first outlet nozzle 231 and a second outlet nozzle 232 for outlet hydrogen from the protective cover 21; the first outlet nozzle 231 is vertically arranged at the top of the protective cover 21 and is connected to the interior of the protective cover 21; a plurality of first outlet nozzles 231 are equidistantly arranged along the long side direction of the protective cover 21; two groups of second outlet nozzles 232 are provided, and the two groups of second outlet nozzles 232 are relatively vertically arranged on both sides of the protective cover 21 and are connected to 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.

[0040] The protective cover 21 is a hollow polygonal shell with an open bottom, and a cushioning airbag 211 is fixedly provided at each corner of the polygonal shell.

[0041] The first outlet nozzle 231 at the top of the protective cover 21 provides a targeted outlet for leaked hydrogen in the event of a small leak from the hydrogen fuel tank 11. The outlet direction of the first outlet nozzle 231 is precisely defined, ensuring that the leaked hydrogen gas is always directed downward, perpendicular to the drone 1. This creates a stable, controllable downward force on the drone 1 only in the longitudinal direction, preventing lateral thrust or rotational disturbances caused by the uncertain flow direction of the leaked gas, thereby ensuring stable and safe flight.

[0042] Furthermore, to address the issue of large-scale hydrogen leakage from the hydrogen fuel tank 11 under high pressure or structural damage, the present invention provides two second discharge nozzles 232 circumferentially disposed on the sidewall of the protective cover 21. These second discharge nozzles 232 are symmetrically distributed and can work together in the event of a large-volume leak, guiding the hydrogen leakage flow unidirectionally, distributing the leaked gas circumferentially and evenly along the periphery. This structure effectively reduces the asymmetric impact of high-pressure hydrogen in the early stages of a leak, avoiding unbalanced forces on the drone 1 due to uneven local pressure relief, thereby ensuring stable operation of the system under extreme operating conditions.

[0043] The first outlet nozzle 231 is used to achieve directional discharge of trace leaked hydrogen, avoiding the influence of lateral disturbance on the flight attitude; the second outlet nozzle 232 is used to construct a circumferentially uniform pressure relief path to ensure the uniformity and controllability of pressure release when dealing with large-scale leakage, thereby effectively improving the safety control capability and flight stability of the drone 1 under hydrogen leakage conditions.

[0044] See also Figure 4 and Figure 9As shown: the guide unit 23 also includes a first one-way valve 233 and a second one-way valve 234 for opening under the first pressure and the second pressure; the first one-way valve 233 and the second one-way valve 234 are coaxially fixedly arranged in the first outlet nozzle 231 and the second outlet nozzle 232 respectively.

[0045] The first one-way valve 233 is set to open at a first preset pressure, and the second one-way valve 234 is set to open at a second preset pressure higher than the first preset pressure. This allows the corresponding outlet channel to be automatically selected and opened according to the different levels of hydrogen pressure in the protective cover 21 when the hydrogen fuel tank 11 leaks: when the leakage 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 reaches the first pressure threshold, the first one-way valve 233 automatically opens, directing the hydrogen to be discharged in a directional manner preferentially through the first outlet nozzle 231; when the leakage continues to increase, causing the pressure to exceed the second pressure threshold, the second one-way valve 234 opens synchronously, and the hydrogen is evenly discharged in a circumferential, multi-point manner through the second outlet nozzles 232 distributed around the circumference of the protective cover 21.

[0046] Through this graded pressure relief control mechanism, intelligent management of hydrogen discharge paths under different leakage levels is achieved, ensuring fast, safe and targeted gas extraction at any leakage intensity, effectively avoiding the risk of disordered hydrogen leakage disturbing the flight posture of the drone 1.

[0047] By providing a first one-way valve 233 and a second one-way valve 234 with different opening pressures, hydrogen can be automatically diverted and discharged according to pressure when leaking, which can achieve both directional diversion of small leaks and circumferential pressure-equalizing discharge of large leaks, thereby improving the flight stability and safety assurance capabilities of the drone 1 during hydrogen fuel leakage.

[0048] See also Figure 4 As shown, the active protection unit 22 is provided with a locking unit 221 for locking the protective cover 21 and the drone 1 in a non-protection state, and an unlocking unit 222 for actively driving the locking unit 221 to unlock in a protection state.

[0049] When the hydrogen fuel tank 11 leaks violently during flight, and the leakage reaches a critical level that affects the flight stability or safe operation of the drone 1, it is necessary to quickly and actively jettison the hydrogen fuel tank 11 to prevent the accident from escalating. At this time, by driving the unlocking unit 222 to control the locking unit 221, the protective cover 21 can be detached from the drone 1, thereby achieving the purpose of jettisoning the protective cover 21 and the hydrogen fuel tank 11 disposed therein.

[0050] Because the hydrogen fuel tank 11 is integrated within the protective cover 21, the protective cover 21, when ejected, carries the hydrogen fuel tank 11 away from the drone 1, enabling rapid separation of the hydrogen fuel tank 11 from the drone 1. This process, without requiring external manual intervention, physically isolates the fuel source in a very short time, reducing the risk of continued hydrogen leaks and effectively preventing safety incidents such as loss of flight control or explosions caused by fuel system anomalies.

[0051] See also Figure 4 As shown: the active protection unit 22 also includes a guide rod 223, a first spring 224, a second spring 225 and an air guide tube 226; the guide rod 223 is vertically fixed on the top of the drone 1, the guide rod 223 is a hollow rod body that is arranged vertically and penetrates the top of the guide rod 223, and a through hole 2231 is radially penetrated at the top of the guide rod 223; the first spring 224 is coaxially arranged in the guide rod 223; the locking unit 221 is coaxially slidably arranged in the guide rod 223 and the bottom is aligned with the first spring 224 abuts against the top; the locking end of the locking unit 221 passes through the through hole 2231 and is arranged toward the outside of the guide rod 223; the second spring 225 is coaxially sleeved and installed outside the guide rod 223; the air guide tube 226 is coaxially arranged on the top of the guide rod 223, one end of the air guide tube 226 is connected to the guide rod 223, and the other end is connected to the guide end of the guide unit 23; the unlocking unit 222 is fixedly arranged in the drone 1 and the unlocking end is connected to the bottom of the locking unit 221.

[0052] When installed, the protective cover 21 is longitudinally limited by the guide rod 223 and securely mounted on the drone 1 frame. The locking unit 221 secures the protective cover 21 to the guide rod 223, thereby reliably securing the protective cover 21 during flight. Specifically, the locking end of the locking unit 221 inserts and engages into the through hole 2231 provided on the guide rod 223, forming a stable, secure connection. Simultaneously, a second spring 225 disposed externally to the guide rod 223 is in a continuously compressed state, constantly exerting an upward force on the protective cover 21, maintaining close contact between the protective cover 21 and the locking end of the locking unit 221, thereby enhancing the securing effect.

[0053] The unlocking unit 222 specifically consists of a pull rope 2221 and a retractor 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 retracting end of the retractor 2222 .

[0054] When it is necessary to actively separate the protective cover 21 from the guide rod 223, the unlocking unit 222 is driven to operate. At this time, the retracting end of the retractor 2222 opens to reel in the pull rope 2221, thereby continuously pulling the locking unit 221 downward longitudinally in the guide rod 223 until the locking end of the locking unit 221 is completely retracted from the through hole 2231 into the guide rod 223, thereby actively unlocking the protective cover 21 and releasing the fixed connection between the protective cover 21 and the guide rod 223.

[0055] Furthermore, to further enhance the system's safety response capabilities in the event of an unexpected leak, the guide rod 223 communicates with a second outlet nozzle 232 located in the upper middle portion of the protective cover 21 via an air duct 226, forming a pressure relief guide channel. When a leak in the hydrogen fuel tank 11 generates significant air pressure within the protective cover 21, this pressure is transmitted to the lower portion of the unlocking unit 222 via the air duct 226. When the pressure reaches a set threshold, the leaked hydrogen gas pushes the unlocking unit 222 downward longitudinally without external control, overcoming the elastic force of the first spring 224 and completing the passive release of the locking end. This allows the protective cover 21 to automatically unlock and quickly disengage under passive control, ensuring the safe isolation response of the drone 1 in the event of an emergency leak.

[0056] See also 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 fixed on the top of the sliding rod 2211; there are two elastic locking rods 2213, and the two elastic locking rods 2213 are relatively fixed in an inclined state on both sides of the sliding rod 2211; the guide seat 2214 is coaxially fixed on the bottom of the sliding rod 2211.

[0057] In the locked state, the front ends of the two elastic locking rods 2213 are arranged in an inclined state through the through hole 2231, thereby achieving a locking effect between the guide rod 223 and the protective cover 21; and since the two elastic locking rods 2213 are 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 tilt toward the sliding rod 2211 and shrink, thereby achieving an 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 clearance-matched, thereby achieving a good pushing effect when the sliding rod 2211 is pushed by the hydrogen leaked from the protective cover 21; the guide seat 2214 is used to axially guide the sliding rod 2211 to slide in the guide rod 223.

[0058] See also Figure 8 As shown: the guide frame 32 is vertically fixed on the bottom of the drone 1; the hydrogen fuel cell 12 is fixed in the guide frame 32; the buffer frame 31 is vertically slidably arranged outside the guide frame 32 and multiple buffer frames are circumferentially arranged along the axis of the guide frame 32; the opening and closing unit 33 is embedded in the guide frame 32.

[0059] The lower protection module 3 also includes a third spring 34 disposed between the guide frame 32 and the buffer frame 31. This third spring 34 provides vertical elastic support. One end of the third spring 34 is fixedly connected to the bottom of the guide frame 32, and the other end is fixedly connected to the top of the buffer frame 31, thereby forming a stable elastic buffer support structure. When compressed, the third spring 34 stores energy and deforms. When released, it provides a longitudinal elastic force to drive the buffer frame 31.

[0060] The opening and closing unit 33 is preferably an electromagnet, embedded and fixed to the outside of the guide frame 32, near the top of the guide frame 32, to facilitate magnetic attraction and release control of the buffer frame 31. In the non-buffering operating state, the buffer frame 31 is magnetically attracted and compressed to the side wall of the guide frame 32 by the electromagnet, maintaining a compact structure and a stable system.

[0061] When a potential impact threat to the hydrogen fuel cell 12 is detected, or when the buffer protection mechanism needs to be activated, the opening and closing unit 33 is driven to release adsorption by controlling the on / off state of the electromagnet. At this time, the compressed third spring 34 quickly releases its stored energy, pushing the buffer frame 31 downward along the axial direction of the guide frame 32, thereby forming an effective buffer gap between the buffer frame 31 and the guide frame 32. Simultaneously, driven by the elastic restoring force of the third spring 34, the buffer frame 31 extends longitudinally, forming a dynamic elastic buffer structure that can absorb and conduct impact energy to the greatest extent when encountering external impact loads, significantly alleviating mechanical shock to the hydrogen fuel cell 12.

[0062] The present invention can not only perform real-time detection on the hydrogen fuel tank but also provide comprehensive protection for the hydrogen fuel tank.

[0063] The above embodiments merely represent one or more embodiments 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 a person skilled in the art may make various modifications and improvements without departing from the scope of the present invention, and these modifications and improvements fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be determined by the appended claims.

Claims

1. A hydrogen fuel protection device for a hydrogen fuel cell for an unmanned aerial vehicle, characterized in that: include: A drone, a hydrogen fuel tank and a hydrogen fuel cell provided on the drone; an upper protection module, through which the hydrogen fuel tank is detachably mounted on the top of the drone; The upper protection module is provided with a protective cover for real-time protection of the hydrogen fuel tank and an active protection unit for actively separating the protective cover from the drone in the protection state; the upper protection module also includes a guiding unit for directional guidance of hydrogen leaked from the hydrogen fuel tank; A lower protection module, wherein the hydrogen fuel cell is detachably mounted below the drone via the lower protection module; the lower protection module is provided with a buffer frame for fully protecting the hydrogen fuel cell in a protective state; the lower protection module further includes a guide frame for longitudinally guiding the buffer frame to slide, and an opening and closing unit for driving the buffer frame to perform buffering; The guide units are vertically arranged outside the protective cover and are arranged in multiple groups along the circumference of the axis of the protective cover; The guide unit is provided with a first guide nozzle and a second guide nozzle for guiding hydrogen out of the protective cover; The first outlet nozzle is vertically arranged on the top of the protective cover and communicates with the interior of the protective cover; a plurality of the first outlet nozzles are equidistantly arranged along the long side of the protective cover; The second outlet nozzles are provided in two groups, and the two groups of second outlet nozzles are relatively perpendicularly arranged on both sides of the protective cover and communicated with the interior of the protective cover; the two groups of second outlet nozzles are equidistantly arranged along the long side direction of the protective cover; The guide 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 coaxially fixedly disposed in the first outlet nozzle and the second outlet nozzle respectively; The active protection unit is provided with a locking unit for locking the protective cover and the drone in a non-protection state and an unlocking unit for actively driving the locking unit to unlock in a protection state.

2. The hydrogen fuel protection device for a hydrogen fuel cell for an unmanned aerial vehicle according to claim 1, characterized in that: The active protection unit also includes a guide rod, a first spring, a second spring and an air guide tube; The guide rod is vertically fixed on the top of the drone, and the guide rod is hollow and penetrates the rod body vertically, and a through hole is radially penetrated on the top of the guide rod; The first spring is coaxially arranged in the guide rod; The locking unit is coaxially slidably disposed in the guide rod, and the bottom thereof abuts against the top of the first spring; the locking end of the locking unit passes through the through hole and is disposed toward the outside of the guide rod; The second spring is coaxially sleeved and mounted outside the guide rod; The air guide tube is coaxially arranged on the top of the guide rod, one end of the air guide tube is connected to the guide rod, and the other end is connected to the guide 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.

3. The hydrogen fuel protection device for a hydrogen fuel cell for an unmanned aerial vehicle according to claim 1, characterized in that: The locking unit includes a sliding rod, a sealing plug, an elastic locking rod and a guide seat; The sealing plug is coaxially fixedly arranged on the top of the sliding rod; There are two elastic locking rods, which are relatively fixedly arranged on both sides of the sliding rod in an inclined state; The guide seat is coaxially fixed to the bottom of the sliding rod.

4. The hydrogen fuel protection device for a hydrogen fuel cell for an unmanned aerial vehicle according to claim 1, characterized in that: 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 a plurality of buffer frames are circumferentially arranged along the axis of the guide frame; The opening and closing unit is embedded in the guide frame.

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