Hydrogen fuel cell unmanned aerial vehicle for offshore deployment with emergency function

Abstract

The application relates to the technical field of unmanned planes, in particular to a hydrogen fuel cell unmanned plane with an emergency function for sea deployment, which comprises a lower part of an unmanned plane body provided with supporting legs; the hydrogen fuel cell unmanned plane further comprises: containing bins which are symmetrically arranged on the two sides of the lower part of the unmanned plane body in pairs and relative to the supporting legs, the two containing bins are located on the outer sides of the supporting legs, hydrogen gas cylinder bodies are arranged in the containing bins, and the lower ends of the supporting legs are lower than the lower ends of the containing bins; pushing mechanisms which are connected with the two containing bins in pairs; and a driving source arranged between the two pushing mechanisms, the driving source is used for driving the two pushing mechanisms to synchronously push the two containing bins to move away from each other. The application improves the floating stability of the unmanned plane on the sea surface, and avoids the unmanned plane from being overturned due to swinging with sea waves.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a hydrogen fuel cell UAV for maritime deployment with emergency response capabilities. Background Technology

[0002] Hydrogen fuel cell drones have significant advantages when operating at sea, mainly in terms of ultra-long endurance, low-temperature resistance, high environmental adaptability, zero carbon emissions, high energy efficiency, lightweight structure, and economy. However, since they need to be deployed at sea, if an accident occurs, the drone will fall into the sea. To prevent the drone from sinking, special designs are required.

[0003] For example, Chinese Patent Publication No. CN117302593B discloses a hydrogen fuel cell drone for rapid deployment and charging at sea, including a drone body frame. A hydrogen fuel cell assembly is located below the drone body frame. The hydrogen fuel cell assembly includes a hydrogen fuel cell compartment and a hydrogen cylinder. A hydrogen cylinder mounting mechanism is located below the hydrogen fuel cell compartment. The hydrogen cylinder mounting mechanism includes symmetrically arranged cylinder connecting arms. Hollow cylinder fixing devices are provided at both ends of the cylinder connecting arms. A cylinder placement cap is provided on both ends of the cylinder fixing device on one side of the cylinder connecting arm. One side of the cylinder placement cap is hinged to both ends of the cylinder connecting arm, and the other side is snapped to the cylinder fixing device. The drone body frame is fixed to the outer surface of the cylinder fixing device.

[0004] While the above solution can ensure that the drone lands on the sea surface in an emergency, the drone will eventually land on the ground. Replacing the traditional support legs with hydrogen cylinders that make contact with the ground below, although it can prevent the drone from sinking to the seabed upon landing, poses a great risk when landing on land. If the impact is too great, it can easily cause the hydrogen cylinder to explode. At the same time, since the drone's body is on top of the hydrogen cylinder, the drone, which floats on the sea surface with the undulating waves, will sway constantly with the waves. In order to prevent the drone from capsizing when swaying with the waves, the volume of the hydrogen cylinder needs to be increased. As a result, the hydrogen cylinders carried on the bottom of existing hydrogen fuel cell drones deployed at sea are much larger than conventional hydrogen cylinders, which has a significant impact on the drone's maneuverability. Summary of the Invention

[0005] To address the aforementioned issues, a hydrogen fuel cell drone for maritime deployment with emergency capabilities is provided. It features two symmetrically positioned housings located outside the outriggers, each housing a hydrogen cylinder. The lower end of the outriggers is lower than the lower end of the housing, effectively preventing damage to the housings and hydrogen cylinders during land takeoffs and landings, thus improving land-based safety. Power is supplied by a drive source, driving two synchronous propulsion mechanisms to push the two housings apart, increasing the support distance when the drone is floating. The housings also increase the contact area with seawater, enhancing the drone's floating stability and preventing it from capsizing due to waves.

[0006] To address the problems of existing technologies, this invention provides a hydrogen fuel cell unmanned aerial vehicle (UAV) for maritime deployment with emergency response capabilities, comprising a UAV body with two symmetrical legs at the bottom; The hydrogen fuel cell drone also includes: The container has two compartments, which are symmetrically arranged on both sides of the lower part of the drone body about the axis of symmetry of the two legs. The two compartments are located outside the legs. The compartments contain hydrogen cylinders. The lower end of the legs is lower than the lower end of the compartments. The propulsion mechanism has two parts, each connected to one of the two containing compartments; A drive source is disposed between the two pushing mechanisms, and the drive source is used to drive the two pushing mechanisms to synchronously push the two receiving chambers away from each other.

[0007] Preferably, the lower part of the driving source is provided with a button for controlling the start of the driving source, and a trigger element that can trigger the button is provided below the button in a vertical direction.

[0008] Preferably, the trigger is a hollow shell structure.

[0009] Preferably, a limit rod is vertically fixed to the upper part of the trigger, and a limit frame is provided at the lower part of the UAV body. The limit rod vertically passes through the limit frame and slides in cooperation with the limit frame.

[0010] Preferably, the driving source is a gas generator.

[0011] Preferably, the actuating mechanism includes: A telescopic sleeve is horizontally fixed on the side wall of the drive source, and the telescopic sleeve is connected to the drive source; A telescopic rod is slidably disposed within the telescopic sleeve along the extension direction of the telescopic sleeve, and the end of the telescopic rod away from the drive source is fixedly connected to the receiving chamber.

[0012] Preferably, a one-way valve is provided between the telescopic sleeve and the drive source.

[0013] Preferably, each of the containing chambers contains at least two hydrogen cylinders arranged horizontally.

[0014] Preferably, the drone has a built-in positioning device.

[0015] Preferably, a warning light is provided on the top of the drone body.

[0016] The advantages of this invention compared to the prior art are: 1. This invention features two symmetrically positioned storage compartments located outside the support legs. Each compartment houses a hydrogen cylinder, with the lower end of the support legs lower than the lower end of the compartment. This effectively prevents damage to the storage compartments and the internal hydrogen cylinders during UAV takeoffs and landings on land, improving safety. Power is supplied by a drive source to simultaneously activate two propulsion mechanisms, pushing the two storage compartments apart and increasing the support distance when the UAV is floating. The increased contact area with seawater by the storage compartments enhances the UAV's floating stability on the sea surface, preventing it from capsizing due to waves. This design eliminates the need to increase the volume of the hydrogen cylinders, balancing floating stability with the UAV's maneuverability.

[0017] 2. By incorporating a vertically movable trigger element, in conjunction with a button at the bottom of the drive source, the drive source is automatically triggered. This ensures that the drive source can be quickly activated after the UAV crashes into the water, thereby pushing the containment chambers apart through a propulsion mechanism and promptly improving floating stability. The trigger element, upon contact with the sea surface after the UAV crashes, moves upward relative to the UAV body using the buoyancy of the seawater, precisely triggering the button. This ensures the timeliness and accuracy of the drive source activation, preventing the UAV from capsizing due to delayed activation and further enhancing the reliability of UAV emergency response at sea, adapting to the needs of complex emergency scenarios at sea.

[0018] 3. By using a gas generator as the driving source, the failure of the container to deploy due to insufficient power or poor transmission is avoided. With the help of a one-way valve, it is ensured that the container will not retract after deployment. The multiple hydrogen cylinders set in the container can not only ensure the stability of the UAV when landing on the sea surface, but also improve its own endurance. At the same time, the emergency function components inside the UAV fuselage and on the top achieve multiple effects such as safe take-off and landing on land, stable floating at sea in emergency situations, and reliable power supply, thus comprehensively ensuring the safety and practicality of the UAV's deployment at sea. Attached Figure Description

[0019] Figure 1 This is a three-dimensional schematic diagram of a hydrogen fuel cell unmanned aerial vehicle (UAV) with emergency response capabilities for maritime deployment according to the present invention. Figure 1 .

[0020] Figure 2This is a three-dimensional schematic diagram of a hydrogen fuel cell unmanned aerial vehicle (UAV) with emergency response capabilities for maritime deployment according to the present invention. Figure 2 .

[0021] Figure 3 This is a three-dimensional schematic diagram of the storage compartment of a hydrogen fuel cell UAV with emergency function for maritime deployment according to the present invention when it is deployed.

[0022] Figure 4 This is a three-dimensional schematic diagram of the hydrogen cylinder being extracted from a hydrogen fuel cell drone with emergency functions for maritime deployment according to the present invention.

[0023] Figure 5 This invention relates to a hydrogen fuel cell unmanned aerial vehicle (UAV) with emergency response capabilities for maritime deployment. Figure 4 A magnified view of a portion of point A in the middle.

[0024] Figure 6 This is a three-dimensional schematic diagram of a hydrogen fuel cell drone for maritime deployment with emergency functions, with the drone's fuselage removed.

[0025] Figure 7 The present invention is a hydrogen fuel cell drone for maritime deployment with emergency functions, which removes the top view of the drone's rear fuselage.

[0026] Figure 8 This invention relates to a hydrogen fuel cell unmanned aerial vehicle (UAV) with emergency response capabilities for maritime deployment. Figure 7 Schematic diagram of cross-section at point BB.

[0027] Figure 9 This is a three-dimensional cross-section of a hydrogen fuel cell drone for maritime deployment with emergency response capabilities, with the drone's fuselage removed.

[0028] Figure 10 This invention relates to a hydrogen fuel cell unmanned aerial vehicle (UAV) with emergency response capabilities for maritime deployment. Figure 9 A magnified view of a portion of point C.

[0029] The following are the labels in the diagram: 1. UAV body; 11. Support legs; 12. Warning light; 2. Storage compartment; 21. Hydrogen cylinder body; 3. Pushing mechanism; 31. Telescopic sleeve; 32. Telescopic rod; 33. One-way valve; 4. Drive source; 41. Button; 5. Trigger; 51. Limit rod; 6. Limit frame. Detailed Implementation

[0030] To further understand the features, technical means, and specific objectives and functions achieved by the present invention, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.

[0031] Reference Figures 1 to 4A hydrogen fuel cell unmanned aerial vehicle (UAV) for maritime deployment with emergency response capabilities, comprising a UAV body 1 with two symmetrical legs 11 at the bottom; The hydrogen fuel cell drone also includes: The two storage compartments 2 are symmetrically arranged on both sides of the lower part of the drone body 1 about the axis of symmetry of the two legs 11. The two storage compartments 2 are located outside the legs 11. The storage compartment 2 contains a hydrogen cylinder body 21. The lower end of the legs 11 is lower than the lower end of the storage compartment 2. The actuating mechanism 3 has two parts and is connected to each of the two receiving compartments 2 respectively; A drive source 4 is disposed between the two push mechanisms 3, and the drive source 4 is used to drive the two push mechanisms 3 to push the two receiving chambers 2 away from each other synchronously.

[0032] The drone body 1 has a built-in hydrogen fuel cell. A hydrogen cylinder 21, located within the housing 2, is connected to the hydrogen fuel cell of the drone body 1 via a connecting pipe. The drive source 4 can be either a gas generator or an electric motor. During manufacturing, different structures or types of drive sources 4 can be selected according to requirements, ensuring that the drive source 4, once activated, can push the housing 2 via the push mechanism 3. When the drive source 4 is pneumatic, such as a gas generator, the push mechanism 3 employs a telescopic structure, including a telescopic sleeve 31 and a telescopic rod 32. The telescopic structure is extended and retracted by gas; when gas is injected into the telescopic sleeve 31, the telescopic rod 32 extends, and the push mechanism 3 extends. Similarly, when the drive source 4 is electric, the push mechanism 3 employs a screw-type structure, where the screw threadedly engages with each of the two housing 2, achieving the effect of driving the two housing 2 away from each other.

[0033] This emergency-capable hydrogen fuel cell drone for maritime deployment takes off from land, which can include offshore platforms, ships, or coastlines. Because the lower ends of the outriggers 11 are lower than the lower ends of the housing 2, the outriggers 11 are in contact with the ground for support during takeoff and landing, while the housing 2 remains stationary. The hydrogen fuel cell built into the drone body 1 is connected to a hydrogen cylinder 21 inside the housing 2 via a connecting pipe. The hydrogen cylinder 21 provides power to the hydrogen fuel cell, ensuring the drone's operation at sea. When the drone needs to make an emergency landing due to fuel shortage or malfunction during maritime deployment, it lands on the sea surface. The outriggers 11 initially contact the sea surface and gradually submerge, while the housing 2 remains in direct contact with the sea surface. The drone body 1 floats on the sea surface via the housing 2. When further improvement in the drone's floating stability is needed, the drive source 4 is activated. The drive source 4 drives two propulsion mechanisms 3 to move synchronously, pushing their respective housings 2 away from each other until the desired stable state is achieved. After the drone floats on the sea surface, it can use its onboard functional components to assist in subsequent salvage operations, ensuring that the drone can be successfully recovered. The drive source 4 can be a gas generator or an electromagnetic elastic device. During manufacturing, the appropriate type of drive source 4 can be selected according to actual needs to ensure that after the drive source 4 is started, it can stably push the container 2 to move through the push mechanism 3.

[0034] By setting up two symmetrical storage compartments 2 about the support legs 11 and located outside the support legs 11, with hydrogen cylinder bodies 21 inside the storage compartments 2, and the lower end of the support legs 11 being lower than the lower end of the storage compartments 2, the problem of hydrogen cylinders being easily damaged by impact and posing safety hazards during land take-off and landing of existing hydrogen fuel cell UAVs deployed at sea is effectively solved. This ensures that only the support legs 11 are in contact with the ground during land take-off and landing of the UAV, avoiding damage to the storage compartments 2 and the internal hydrogen cylinder bodies 21, and improving the safety of land take-off and landing; by setting up two propulsion mechanisms 3 and a drive source 4, the drive source 4 can drive the two propulsion mechanisms 3. Simultaneously pushing the two containment chambers 2 away from each other effectively solves the problems of insufficient stability, easy capsizing, and reduced maneuverability of existing UAVs floating on the sea surface due to increased hydrogen cylinder volume. By increasing the contact surface with seawater using containment chambers 2, initial floating stability is ensured. By moving the containment chambers 2 away from each other, the support spacing is further increased, significantly improving floating stability without increasing the volume of a single hydrogen cylinder 21, thus balancing floating stability and maneuverability. At the same time, the drive source 4 can be selected from different types according to needs, improving the versatility and flexibility of the device, reducing manufacturing and usage costs, and adapting to different offshore deployment scenarios.

[0035] Reference Figure 10 The lower part of the driving source 4 is provided with a button 41 for controlling the start of the driving source 4, and a trigger 5 that can trigger the button 41 is provided below the button 41 in a vertical direction.

[0036] When the drone makes an emergency landing on the sea surface, the outriggers 11 first contact the sea surface and gradually submerge. Then, the trigger 5 contacts the sea surface. Since the trigger 5 can move vertically and the drone body 1 continues to sink, the trigger 5, supported by the seawater, moves upward relative to the drone body 1. Finally, the upper part of the trigger 5 presses the button 41, triggering it. The button 41 controls the start of the drive source 4, which in turn drives two propulsion mechanisms 3 to simultaneously push the two containment chambers 2 away from each other, thus improving the drone's floating stability. This structure eliminates the need for manual activation of the drive source 4, achieving automatic triggering and solving the problems of delayed response and inability to promptly improve floating stability after manual activation. It ensures that the drone can quickly adjust its attitude after an emergency landing, preventing capsizing due to untimely attitude adjustment. It also simplifies the operation process and improves the timeliness and reliability of emergency response.

[0037] Reference Figures 8 to 10 The trigger element 5 is a hollow shell structure.

[0038] The trigger 5 adopts a hollow shell structure, giving it a certain degree of buoyancy. When the drone makes an emergency landing on the sea surface, the trigger 5 will not sink into the water due to its own buoyancy and will be stably supported on the sea surface. As the drone body 1 continues to sink, the trigger 5 moves upward relative to the drone body 1. When the upper part of the trigger 5 contacts the button 41 and presses down the button 41, the drive source 4 is activated, ensuring the smoothness and accuracy of the triggering action of the drive source 4. This solves the problem that the trigger 5 is prone to sinking into the sea due to its excessive weight and cannot effectively trigger the button 41. At the same time, the hollow shell structure is lightweight, does not increase the overall weight of the drone, and does not affect the drone's maneuverability, thus balancing the requirements of trigger reliability and drone lightweight design.

[0039] Reference Figure 5 and Figure 9 The upper part of the trigger 5 is vertically fixed with a limiting rod 51, and the lower part of the UAV body 1 is provided with a limiting frame 6. The limiting rod 51 vertically passes through the limiting frame 6 and slides in cooperation with the limiting frame 6.

[0040] The limiting rod 51 at the upper part of the trigger 5 vertically penetrates the bottom of the limiting frame 6 at the lower part of the UAV body 1, and the two slide together, limiting and guiding the vertical movement of the trigger 5. When the UAV falls into the water in an emergency, as the trigger 5 moves upward relative to the UAV body 1 under the buoyancy of the seawater, the limiting rod 51 slides vertically along the limiting frame 6, preventing the trigger 5 from shifting or tilting during movement. This ensures that the trigger 5 can accurately align with the button 41 and trigger it, guaranteeing the accuracy of the start-up of the drive source 4. This improves the reliability of the automatic triggering of the drive source 4, while the limiting structure is simple, does not affect the normal movement of the trigger 5, and does not increase the structural complexity of the UAV.

[0041] Reference Figures 1 to 10 The driving source 4 is a gas generator.

[0042] The drive source 4 uses a gas generator. When button 41 is triggered, the gas generator starts and quickly generates gas. The generated gas is simultaneously delivered to the two push mechanisms 3. The thrust of the gas drives the push mechanisms 3 to move, thereby pushing the two housings 2 away from each other, increasing the support distance when the drone floats and improving its floating stability. The gas generator has a fast response speed and can generate sufficient thrust in a short time to ensure that the housings 2 deploy quickly. This solves the problems of delayed response of the drive source 4, insufficient thrust causing the housings 2 to fail to deploy in time, and the drone being prone to tipping over. At the same time, the gas generator has a compact structure and is lightweight, which is suitable for the lightweight requirements of drones. It also does not require a complex energy storage structure, reducing the maintenance cost and failure probability of the device.

[0043] Reference Figure 6 The driving mechanism 3 includes: The telescopic sleeve 31 is horizontally fixed on the side wall of the drive source 4, and the telescopic sleeve 31 is connected to the drive source 4; The telescopic rod 32 is slidably disposed inside the telescopic sleeve 31 along the extension direction of the telescopic sleeve 31, and the end of the telescopic rod 32 away from the drive source 4 is fixedly connected to the receiving chamber 2.

[0044] The pushing mechanism 3 consists of a telescopic sleeve 31 and a telescopic rod 32. The telescopic sleeve 31 is horizontally fixed to the side wall of the drive source 4 and is connected to the drive source 4. The telescopic rod 32 is slidably disposed inside the telescopic sleeve 31 and fixedly connected to the receiving chamber 2. When the gas generator starts and generates gas, the gas enters the telescopic sleeve 31 through the connecting channel. Under the thrust of the gas, the telescopic rod 32 slides outward along the extension direction of the telescopic sleeve 31, thereby pushing the receiving chamber 2 to move horizontally. The two pushing mechanisms 3 act synchronously, so that the two receiving chambers 2 move away from each other.

[0045] By cooperating with the telescopic sleeve 31 and the telescopic rod 32, the thrust of the gas is converted into the horizontal moving force of the container 2. The transmission efficiency is high, and the horizontal transmission can ensure that the container 2 moves smoothly in the preset direction, avoiding tilting or jamming during the movement of the container 2. This solves the problems of unstable transmission of the push mechanism 3 and unsmooth unfolding of the container 2. At the same time, the structure is simple, occupies little space, and is compatible with the installation space under the drone without affecting the overall structural layout of the drone.

[0046] Reference Figure 6 A one-way valve 33 is provided between the telescopic sleeve 31 and the drive source 4.

[0047] A one-way valve 33 is positioned between the telescopic sleeve 31 and the drive source 4 to restrict the airflow direction, allowing only the gas generated by the drive source 4 to flow into the telescopic sleeve 31 while preventing the gas in the telescopic sleeve 31 from flowing back to the drive source 4. When the gas generator generates gas to push the telescopic rod 32 to unfold the housing 2, the two housings 2 will be impacted by the waves due to the undulating sea surface, generating a reverse force. At this time, the one-way valve 33 can prevent the gas in the telescopic sleeve 31 from flowing back, preventing the housing 2 from retracting under the push of the waves, preventing the repeated extension and retraction of the housing 2 from causing a decrease in the floating stability of the UAV, further improving the stability and reliability of the UAV floating on the sea surface, ensuring that the housing 2 can maintain a stable support spacing after unfolding, and preventing the UAV from capsizing due to the extension and retraction of the housing 2.

[0048] Reference Figures 1 to 10 Each of the aforementioned compartments 2 contains at least two hydrogen cylinder bodies 21 arranged horizontally.

[0049] Each containment chamber 2 has at least two hydrogen cylinders 21 arranged horizontally. This increases the hydrogen storage capacity, extends the drone's endurance at sea, and fully leverages the long-range capability of hydrogen fuel cell drones, solving the problem of insufficient hydrogen storage in a single hydrogen cylinder 21, which affects the drone's endurance during deployment at sea. Furthermore, the horizontal arrangement of multiple hydrogen cylinders 21 further increases the contact area between the containment chamber 2 and the seawater, improving buoyancy and floating stability. The even distribution of multiple hydrogen cylinders 21 also ensures more balanced stress distribution on the containment chamber 2, preventing tilting due to uneven stress and further guaranteeing the drone's stability on the sea surface. Additionally, the multiple hydrogen cylinders 21 provide mutual backup; if one cylinder 21 fails, the others can still provide energy to the hydrogen fuel cell, enhancing the reliability of the drone's operation.

[0050] Reference Figures 1 to 10 The unmanned aerial vehicle (UAV) body 1 has a built-in positioning device.

[0051] The drone body 1 has a built-in positioning device. When the drone falls into the water in an emergency and floats on the sea surface, the positioning device will automatically activate and send out a positioning signal. Salvage personnel can quickly locate the drone's position based on this positioning signal, which will facilitate timely salvage operations and prevent the drone from being lost due to the inability to locate it, thus reducing the loss of the drone. At the same time, the positioning device is built into the drone body 1 and will not be corroded by sea salt spray or waves, ensuring the stability and accuracy of the positioning signal and improving the convenience and efficiency of salvage operations.

[0052] Reference Figure 1 and Figure 3 Warning lights 12 are provided on the top of the drone body 1.

[0053] A warning light 12 is installed on the top of the drone body 1. When the drone falls into the water and floats in an emergency at sea, the warning light 12 automatically activates and emits a warning signal. In the marine environment, it can be quickly identified by salvage personnel, especially in low light or complex sea conditions, providing clear guidance and assisting salvage personnel in quickly locating the drone. This solves the problems of drones being difficult to identify and salvage taking a long time in complex marine environments and with poor visibility, further improving salvage efficiency. At the same time, the warning light 12 is located on the top of the drone body 1, making it less susceptible to seawater immersion and ensuring stable operation, guaranteeing continuous output of the warning signal and providing reliable support for salvage operations.

[0054] Working principle: When deploying a drone at sea, it initially takes off from land, such as a sea platform, ship, or coastline. The bottom of the outrigger 11 is lower than the bottom of the housing 2, ensuring that the housing 2 does not directly contact the ground during takeoff and landing, thus preventing damage. When the drone needs to make an emergency landing at sea due to fuel shortage or malfunction, the housing 2 makes direct contact with the sea surface. In this case, the bottom of the outrigger 11 is submerged in the seawater, and the drone body 1 floats on the sea surface through the housing 2. The housing 2, which covers the hydrogen cylinder 21, protects the hydrogen cylinder 21, improving safety. Furthermore, since each housing 2 contains at least two hydrogen cylinders 21 arranged horizontally, the contact area between each housing 2 and the seawater is increased, thereby improving the stability of the drone when landing on the sea surface.

[0055] As the drone descends, the outriggers 11 first contact the sea surface and gradually submerge. Then, the trigger 5 contacts the sea surface. The bottom of the trigger 5 is lower than the bottom of the housing 2, but higher than the bottom of the outriggers 11. Because the trigger 5 is a hollow shell structure, it does not submerge due to buoyancy after contacting the sea surface. The drone body 1 continues to descend. At this time, the trigger 5, lifted by the buoyancy of the seawater, moves upward relative to the drone body 1. The drone body 1 approaches the button 41 and eventually presses it. In this invention, the driving source 4 is a gas generator. The button 41 is used to control the gas generator's activation. After the trigger 5 presses the button 41, the gas generator starts and generates gas. The gas enters the two pushing mechanisms 3. When the gas enters the pushing mechanism 3, it first passes through the one-way valve 33 and then enters the telescopic sleeve 31. Under the pushing action of the gas, the gas moves upward through the telescopic sleeve 31. The telescopic rod 32 inside pushes the container 2 to extend. The two container 2 move away from each other under the action of the corresponding telescopic rods 32 in the two push mechanisms 3, thereby further improving the stability of the UAV when floating on the sea surface. The one-way valve 33 set between the telescopic sleeve 31 and the drive source 4 is used to restrict the flow direction of the airflow. That is, the gas generated in the drive source 4 can only flow into the telescopic sleeve 31 and cannot flow back from the telescopic sleeve 31 to the drive source 4. This is because the drive source 4 may be slightly damaged after generating gas, and the sea surface is constantly undulating, which causes the relative force on the two extended container 2 to be in a state of constant fluctuation. If the one-way valve 33 is not set and the drive source 4 is damaged, the waves will push the extended container 2 to retract in the opposite direction, causing the container 2 to repeatedly extend and retract under the action of the waves, which will greatly reduce the stability of the UAV floating on the sea surface. Therefore, the setting of the one-way valve 33 is very necessary.

[0056] Once the drone is floating on the sea surface, the positioning device built into the drone body 1 emits a positioning signal, which is then used by salvage personnel to retrieve the drone. At the same time, the warning light 12 installed on the drone body 1 is also activated, enabling personnel to quickly identify the drone when approaching the drone body 1, thus improving salvage efficiency.

[0057] The above embodiments only illustrate one or more implementations of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of protection of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the appended claims.

Claims

1. A hydrogen fuel cell unmanned aerial vehicle (UAV) for maritime deployment with emergency response capabilities, comprising a UAV body (1) with two symmetrical legs (11) at the bottom. Its features are, The hydrogen fuel cell drone also includes: The container (2) has two compartments and is symmetrically arranged on both sides of the lower part of the UAV body (1) about the axis of symmetry of the two legs (11). The two compartments (2) are located outside the legs (11). The compartments (2) contain hydrogen cylinder bodies (21). The lower end of the legs (11) is lower than the lower end of the compartments (2). The propulsion mechanism (3) has two parts and is connected to the two receiving compartments (2) respectively; A drive source (4) is disposed between the two push mechanisms (3), and the drive source (4) is used to drive the two push mechanisms (3) to push the two receiving chambers (2) away from each other synchronously.

2. The hydrogen fuel cell drone with emergency response capabilities for maritime deployment according to claim 1, characterized in that, The lower part of the drive source (4) is provided with a button (41) for controlling the start of the drive source (4), and a trigger (5) that can trigger the button (41) is provided below the button (41) in a vertical direction.

3. A hydrogen fuel cell drone with emergency response capabilities for maritime deployment according to claim 2, characterized in that, The trigger (5) is a hollow shell structure.

4. A hydrogen fuel cell drone with emergency response capabilities for maritime deployment, as described in claim 2 or 3, characterized in that, A limit rod (51) is vertically fixed on the upper part of the trigger (5), and a limit frame (6) is provided on the lower part of the drone body (1). The limit rod (51) passes vertically through the limit frame (6) and slides with the limit frame (6).

5. A hydrogen fuel cell drone with emergency response capabilities for maritime deployment according to claim 4, characterized in that, The driving source (4) is a gas generator.

6. A hydrogen fuel cell drone with emergency response capabilities for maritime deployment according to claim 5, characterized in that, The propulsion mechanism (3) includes: The telescopic sleeve (31) is horizontally fixed on the side wall of the drive source (4), and the telescopic sleeve (31) is connected to the drive source (4); The telescopic rod (32) is slidably disposed inside the telescopic sleeve (31) along the extension direction of the telescopic sleeve (31), and the end of the telescopic rod (32) away from the drive source (4) is fixedly connected to the receiving chamber (2).

7. A hydrogen fuel cell drone with emergency response capabilities for maritime deployment according to claim 6, characterized in that, A one-way valve (33) is provided between the telescopic sleeve (31) and the drive source (4).

8. A hydrogen fuel cell drone with emergency response capabilities for maritime deployment according to claim 1, characterized in that, Each of the aforementioned compartments (2) contains at least two hydrogen cylinder bodies (21) arranged horizontally.

9. A hydrogen fuel cell drone with emergency response capabilities for maritime deployment according to claim 1, characterized in that, The UAV body (1) has a built-in positioning device.

10. A hydrogen fuel cell drone with emergency response capabilities for maritime deployment according to claim 1, characterized in that, The top of the drone body (1) is equipped with a warning light (12).

Images