A hydrogen fuel cell drone for rapid deployment of offshore charging

Abstract

The application discloses a hydrogen fuel cell unmanned aerial vehicle for quickly deploying offshore charging and belongs to the technical field of unmanned aerial vehicles. The hydrogen fuel cell unmanned aerial vehicle comprises an unmanned aerial vehicle body frame, a hydrogen fuel cell assembly is arranged below the unmanned aerial vehicle body frame, the hydrogen fuel cell assembly comprises a hydrogen fuel cell bin and a hydrogen cylinder, a hydrogen cylinder mounting mechanism is arranged below the hydrogen fuel cell bin, the hydrogen cylinder mounting mechanism comprises symmetrically-arranged cylinder connecting arms, hollow cylinder fixing devices are arranged on both ends of the cylinder connecting arms, cylinder placing port covers are arranged on the cylinder fixing devices on both ends of the cylinder connecting arms on one side, and the cylinder placing port covers are hinged to both ends of the cylinder connecting arms on one side, respectively. The technical scheme is used to solve the problem that offshore communication equipment cannot respond in time, and the problem that when an unmanned aerial vehicle is used for energy supplementing operation at sea, an additional floating system needs to be arranged, so that the weight of the unmanned aerial vehicle is large and the endurance of the unmanned aerial vehicle is short.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of unmanned aerial vehicles, and particularly relates to a hydrogen fuel cell unmanned aerial vehicle for rapid deployment of sea charging. BACKGROUND

[0002] Due to the wide range, high temporality and long distance from the shore of the temporary communication equipment on the sea, the energy supplement needs to be fast and timely. The conventional ship transportation energy supplement response is slow and not timely, and the economic benefit of the long-distance transportation of the small-power power supply energy is poor. The application of the conventional lithium battery unmanned aerial vehicle to the energy supplement of the temporary communication equipment on the sea has the problems of short endurance time, less energy supplement and the like due to the wide range and long distance of the temporary communication equipment on the sea, and the additional dead weight of the additional design of the sea floating stabilizing device further weakens the endurance of the unmanned aerial vehicle. SUMMARY

[0003] Therefore, the application aims to provide a hydrogen fuel cell unmanned aerial vehicle for rapid deployment of sea charging, so as to solve the problem of slow response and untimely supplement of the conventional ship transportation energy supplement, and the problem of the endurance of the unmanned aerial vehicle being difficult to meet the energy supplement demand in the prior art.

[0004] To achieve the above-mentioned purpose, the application provides the following technical scheme.

[0005] The hydrogen fuel cell unmanned aerial vehicle for rapid deployment of sea charging comprises an unmanned aerial vehicle body frame, a hydrogen fuel cell assembly arranged below the unmanned aerial vehicle body frame, a hydrogen fuel cell compartment and a hydrogen cylinder arranged in the hydrogen fuel cell assembly, a hydrogen cylinder mounting mechanism arranged below the hydrogen fuel cell compartment, symmetrically arranged cylinder connecting arms, hollowly arranged cylinder fixing devices arranged on both ends of the cylinder connecting arms, cylinder placing port covers arranged on the cylinder fixing devices on both ends of the cylinder connecting arms on one side, and the cylinder placing port covers being respectively hinged to both ends of the cylinder connecting arms on one side and being buckled to the cylinder fixing devices on the other side.

[0006] Further, the unmanned aerial vehicle body frame comprises a control electrical compartment, arms, an arm motor, a foot stand and a propeller, the arms are arranged at four corners of the control electrical compartment and are fixedly connected to the outer surface of the control electrical compartment at one end, the arm motor is arranged on the other end of the arm, the propeller is connected to the output end of the arm motor, the foot stand is arranged on the outer surface of the cylinder fixing device, the hydrogen fuel cell compartment is electrically connected to the control electrical compartment, and the hydrogen fuel cell compartment and the hydrogen cylinder are connected through an electrical comprehensive pipeline.

[0007] Further, the hydrogen fuel cell compartment and the control electrical compartment are electrically connected through the quick plug connector, which has the advantage that the quick plug connector is used for electrical connection, so that each component can be independently modularized, and then quickly connected and assembled when needed.

[0008] Further, the hydrogen fuel cell compartment is provided with a fuel cell air inlet and a fuel cell air outlet on the outer side.

[0009] Further, the hydrogen fuel cell compartment is provided with a battery, which is electrically connected to the output end of the hydrogen fuel cell compartment and electrically connected to the control electrical compartment, which has the advantage that the remaining amount of power generated by the hydrogen fuel cell compartment after supplying the unmanned aerial vehicle can be used to charge the battery, thereby increasing the system safety redundancy as a backup energy source, and the setting of the battery can be used as an energy system power extender to play the role of peak shaving and valley filling of the whole machine power, so that the stack system can always maintain a high efficiency working state.

[0010] Further, the hydrogen fuel cell compartment is provided with a charging mechanical arm, the end of the charging mechanical arm is provided with a charging interface, the charging interface is electrically connected to the battery, and the side of the hydrogen fuel cell compartment above the charging mechanical arm is provided with a visual positioning device, which has the advantage that the visual positioning device can position the position of the offshore charging connector, assist in controlling the charging mechanical arm to accurately insert the charging interface into the charging position, and overcome the problem of difficulty in charging the unmanned aerial vehicle due to the shaking of the offshore charging platform.

[0011] Further, the inside of the gas cylinder connecting arm is provided with an inwardly arranged first through slot, the inside of the first through slot is provided with a rotating shaft rotatably connected to the end of the gas cylinder connecting arm, one end of the rotating shaft is provided with a first belt pulley, the outside of the gas cylinder connecting arm above the first belt pulley is provided with a second through slot, the outside of the second through slot is provided with a rotating motor, the rotating motor is electrically connected to the control electrical compartment, the output end of the rotating motor is provided with a second belt pulley, the first belt pulley and the second belt pulley are provided with a driving belt, the rotating shaft arranged in the gas cylinder connecting arm is respectively wound with a traction rope and a floating water-absorbing soft plate, one end of the traction rope and the floating water-absorbing soft plate is fixed to the rotating shaft, and the other end is fixedly connected.

[0012] When the unmanned aerial vehicle needs to float on the sea surface for operation, by controlling the rotation of the rotating motor arranged on both sides, the traction rope can be retracted, and at the same time, the floating water-absorbing soft plate wound on the rotating shaft is pulled out until the floating water-absorbing soft plate covers the space between the gas cylinder connecting arms, at this time, the floating water-absorbing soft plate is in contact with seawater, and the floating water-absorbing soft plate will absorb water, resulting in an increase in the overall mass of the unmanned aerial vehicle, which can increase the draught of the unmanned aerial vehicle, thereby ensuring the stability of the unmanned aerial vehicle when floating on the sea surface (because the unmanned aerial vehicle is usually designed to reduce weight in order to meet the long endurance, but the stability of the unmanned aerial vehicle on the sea surface is poor after weight reduction), and improving the operation effect (such as shooting operation).

[0013] When the unmanned aerial vehicle needs to take off from the sea surface, only the direction operation rotating motor is needed to reset the traction rope and the floating water-absorbing soft plate, and in the resetting process, the water in the floating water-absorbing soft plate is squeezed out due to the extrusion between the first through groove and the rotating shaft, thereby realizing weight reduction take-off, and it needs to be noted that in the take-off state of the unmanned aerial vehicle, the floating water-absorbing soft plate is completely wound and retracted on the rotating shaft, and only the traction rope exists between the gas cylinder connecting arms, and such a mode can reduce the wind resistance in the flight process.

[0014] Further, the floating water-absorbing soft plate comprises a waterproof bubble layer and a sponge layer, and the waterproof bubble layer is arranged above and bonded with the sponge layer, which has the advantages that the waterproof bubble layer can play a role in isolating seawater evaporation to avoid water entering the upper electrical components, and the sponge layer is used for sufficient water absorption.

[0015] The beneficial effects of the present application are:

[0016] (1) The whole machine system is high in automation degree, saves a large amount of labor cost, is good in system cooperation, convenient in practical operation, and high in integration degree, and the integrated charging mechanical arm and visual auxiliary system solve the problem that the charging port is not easy to dock due to the shaking of the unmanned aerial vehicle on the sea.

[0017] (2) The unmanned aerial vehicle adopts a hydrogen fuel cell system as the main energy of the whole machine and a device charging and generating module, the whole machine is pollution-free, low-carbon and environmentally friendly, and the only emission is water.

[0018] (3) The large-volume hydrogen cylinder of the unmanned aerial vehicle is used as the unmanned aerial vehicle floating stability system to increase the stability of the unmanned aerial vehicle on the sea surface, since the gas cylinder is made of aluminum inner container and composite fiber with high strength, and at the same time, the unmanned aerial vehicle uses the gas cylinder as the unmanned aerial vehicle body structure part to enhance the strength of the unmanned aerial vehicle body and reduce the weight of the unmanned aerial vehicle.

[0019] (4) The hydrogen fuel cell system has a comprehensive energy density 2-3 times that of conventional lithium batteries, the endurance time of the unmanned aerial vehicle is increased, and at the same time, the gas cylinder is used as the unmanned aerial vehicle body structure to further reduce the weight of the unmanned aerial vehicle and increase the task range and endurance time of the unmanned aerial vehicle.

[0020] (5) The unmanned aerial vehicle in the technical solution can be used as a temporary electric energy supply point of a marine route for rapid deployment.

[0021] Additional advantages, objects, and features of the application will be set forth in part by the description that follows, and in part will become apparent to those skilled in the art upon examination of the following specification or can be learned by the practice of the application. The advantages of the application can be realized and attained by the instrumentalities set forth in the appended claims. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to make the objectives, technical solutions and beneficial effects of the present application clearer, the present application provides the following drawings for description:

[0023] Fig. 1 is a perspective view of the hydrogen fuel cell unmanned aerial vehicle of the present application;

[0024] Fig. 2 is a perspective view of the hydrogen fuel cell unmanned aerial vehicle of the present application from another angle;

[0025] Fig. 3 is a perspective view of the hydrogen fuel cell unmanned aerial vehicle of the present application from another angle;

[0026] Fig. 4 is a perspective view of the hydrogen fuel cell unmanned aerial vehicle of the present application from another angle;

[0027] Fig. 5 is a perspective view of the hydrogen fuel cell unmanned aerial vehicle of the present application from another angle;

[0028] The drawings are marked as follows:

[0029] 1 - control electrical bin, 2 - arm motor, 3 - propeller, 4 - hydrogen fuel cell bin, 5 - charging mechanical arm, 6 - gas cylinder fixing device, 7 - gas cylinder connecting arm, 8 - hydrogen cylinder, 9 - electrical comprehensive pipeline, 10 - fuel cell exhaust port, 11 - quick plug connector, 12 - charging interface, 13 - foot stand, 14 - arm, 15 - gas cylinder placement port cover, 16 - rotating shaft, 17 - visual positioning device, 18 - fuel cell air inlet, first through slot 19, rotating motor 20, first pulley 21, drive belt 22, second through slot 23, rotating shaft 24, traction rope 25, floating water absorption soft plate 26, waterproof bubble layer 27, sponge layer 28. DETAILED DESCRIPTION

[0030] As Figs. 1-2The application is a fast-deployable offshore floating hydrogen fuel cell unmanned aerial vehicle, which comprises an offshore floating stabilizing device with a hydrogen storage component as the main body, a hydrogen fuel cell energy component with a charging mechanical arm attached to the lower part of the unmanned aerial vehicle power frame, which can access the power equipment through visual light sensing guidance, a four-rotor power system unmanned aerial vehicle system, and three system components are modularly designed for fast assembly and replacement.

[0031] Specifically, the control electrical appliance compartment 1, the arm 14, and the foot stand 13 are mutually fixed and connected to form the unmanned aerial vehicle body frame. The gas cylinder fixing device 6 is fixedly connected with the unmanned aerial vehicle foot stand 13 to form a whole with the unmanned aerial vehicle, two hydrogen storage cylinders 8 are installed and fixed on the unmanned aerial vehicle through the gas cylinder fixing device 6 as the offshore floating stabilizing device of the unmanned aerial vehicle, which has the characteristics of large volume and heavy weight, so that the unmanned aerial vehicle has higher stability on the sea surface. The hydrogen fuel cell compartment 4 is fixed with the foot stand 13 and connected with the gas cylinder fixing device 6 through the electrical comprehensive pipeline 9, and the gas pipeline and the cable are integrated. The gas cylinder placing cover 15 is installed in front of the gas cylinder fixing device 6 through the rotating shaft 16 or the pin shaft as a gas cylinder replacement installation compartment opening, which facilitates quick replacement of the gas cylinder, and the other side is connected by buckling. Four propellers 3 are installed on the motor 2 of the arm 14 in a quadrilateral, and the motor 2 of the arm 14 is located at the end of the arm 14. The hydrogen fuel cell compartment 4 is located at the lower middle part of the unmanned aerial vehicle frame and connected to the control electrical appliance compartment 1 through the quick plug connector 11, which is also an electrical plug-in interface, which is a prior art. The charging interface 12 is located at the port of the charging mechanical arm 5 and at the lower part of the hydrogen fuel cell compartment 4. The charging mechanical arm 5 provides control assistance through the visual positioning device 17, which facilitates the charging mechanical arm 5 to align with the charging interface 12. The fuel cell exhaust port 10 is located on both sides of the fuel cell compartment to remove the heat generated by the fuel cell system, and the fuel cell air inlet 18 is located in front of the fuel cell compartment.

[0032] It should be noted that the gas cylinder fixing device 6 in this specific embodiment refers to a cylindrical sleeve component with one end closed, and the hydrogen cylinder 8 is placed in the two cylindrical sleeve components provided on one side, and the closed end of one of the cylindrical sleeve components is provided with a gas cylinder placing cover 15.

[0033] Working process description:

[0034] The unmanned aerial vehicle can be deployed on the coastline or on the ship, receive a temporary power supply task, determine the coordinates of the power supply task target, automatically complete self-checking, start the hydrogen fuel cell compartment 4 and the rotor power system, fly to the task coordinates, land according to the planned route next to the sea task target, and stabilize the unmanned aerial vehicle posture in real time through the rotor. The unmanned aerial vehicle extends the charging mechanical arm 5 through the visual positioning device 17, analyzes the equipment charging port feature identifier, adjusts the position of the charging mechanical arm 5 to connect the charging port and the equipment. The fuel cell compartment continues to work to output power to charge the equipment. If there is a next task target point, the unmanned aerial vehicle analyzes the hydrogen cylinder 8 pressure value to calculate the remaining hydrogen amount. If the remaining hydrogen amount is sufficient to perform the next task target, the unmanned aerial vehicle directly takes off from the sea surface according to the route to reach the next task target point. If the hydrogen cylinder needs to be replaced, the unmanned aerial vehicle flies back to the base, the base personnel opens the hydrogen cylinder placement port cover 15 of the hydrogen cylinder fixing device 6, removes the old hydrogen cylinder 8, replaces a full hydrogen cylinder 8, and closes it. The unmanned aerial vehicle continues to perform the next target point to perform the charging and power supply task.

[0035] As shown in Figs. 3-5 The inside of the hydrogen cylinder connecting arm 7 is provided with a first through slot 19 arranged inwardly. The inside of the first through slot 19 is provided with a rotating shaft 24 rotatably connected with the end of the hydrogen cylinder connecting arm 7. One end of the rotating shaft 24 is provided with a first belt pulley 21. The outside of the hydrogen cylinder connecting arm 7 above the first belt pulley 21 is provided with a second through slot 23. The outside of the second through slot 23 is provided with a rotating motor 20. The rotating motor 20 is electrically connected with the control electric appliance compartment 1. The output end of the rotating motor 20 is provided with a second belt pulley. The first belt pulley 21 and the second belt pulley are provided with a driving belt 22. The rotating shaft 24 arranged in the hydrogen cylinder connecting arm 7 is respectively wound with a traction rope 25 and a floating water absorption soft plate 26. One end of the traction rope 25 and the floating water absorption soft plate 26 is respectively fixed to the rotating shaft 24. The other end of the traction rope 25 and the floating water absorption soft plate 26 is fixedly connected.

[0036] When the unmanned aerial vehicle needs to float on the sea surface for operation, the traction rope 25 can be retracted by rotating the rotating motor 20 arranged on both sides, and the floating water absorption soft plate 26 wound on the rotating shaft 24 is pulled out at the same time, until the floating water absorption soft plate 26 lays and covers the space between the hydrogen cylinder connecting arms 7. At this time, the floating water absorption soft plate 26 is in contact with seawater, and the floating water absorption soft plate 26 will absorb water, resulting in an increase in the overall mass of the unmanned aerial vehicle, which can increase the draft of the unmanned aerial vehicle, thereby ensuring the stability of the unmanned aerial vehicle when floating on the sea surface (because the unmanned aerial vehicle is usually designed to reduce weight to meet long endurance, and the stability of the unmanned aerial vehicle on the sea surface is poor after weight reduction), improving the operation effect (such as shooting operation); at the same time, the floating water absorption soft plate 26 is unfolded, which can also avoid seawater splashing onto the electronic components above.

[0037] When the unmanned aerial vehicle needs to take off from the sea surface, only the direction operation rotating motor 20 is needed to reset the traction rope 25 and the floating water-absorbing soft plate 26, and in the resetting process, the water of the floating water-absorbing soft plate 26 will be squeezed out due to the extrusion between the first through groove 19 and the rotating shaft 24, thereby realizing weight reduction take-off. It should be noted that in the take-off state of the unmanned aerial vehicle, the floating water-absorbing soft plate 26 is completely wound and retracted on the rotating shaft 24, and only the traction rope 25 exists between the gas cylinder connecting arms 7. In this way, the wind resistance in the flight process can be reduced.

[0038] The floating water-absorbing soft plate 26 includes a waterproof bubble layer 27 and a sponge layer 28, the waterproof bubble layer 27 is arranged above and bonded with the sponge layer 28, the waterproof bubble layer 27 can play a role in isolating seawater evaporation to avoid water entering the upper electrical components, and the sponge layer 28 is used for sufficient water absorption.

[0039] The technical solution uses a hydrogen fuel cell system to power the unmanned aerial vehicle, and uses the unmanned aerial vehicle to achieve the purpose of rapid deployment in a large range. A large-volume hydrogen tank 8 is used as a sea floating device, and the unmanned aerial vehicle rotor auxiliary control system and the floating water-absorbing soft plate mechanism are used together to maintain the stability of the unmanned aerial vehicle platform. After reaching the deployment point, charging connection is carried out, and the hydrogen fuel cell system provides long-term continuous power for the demand equipment. The sea charging device and the unmanned aerial vehicle applied to the sea communication are prior art, and can be referred to CN202222783733.X: A wireless charging platform for a sea unmanned aerial vehicle; CN202110935697.1: A mooring unmanned aerial vehicle signal base station based on a sea buoy; CN202021038241.2: An unmanned aerial vehicle capable of self-power supply and suitable for sea search; CN202011181131.6: A sea new energy charging pile capable of limiting and floating.

[0040] It should be noted that in the technical solution, the structure innovation part is specifically protected, and the specific electrical connection and control part can be realized by the prior art, and the method and equipment for charging the storage battery by the hydrogen fuel cell compartment have been applied for another patent, so no more details are given here.

[0041] Finally, it should be noted that the above preferred embodiments are only used to illustrate the technical solutions of the present application and are not limiting. Although the present application has been described in detail through the above preferred embodiments, those skilled in the art should understand that various changes can be made in form and details without departing from the scope defined by the claims of the present application.

Claims

1. A hydrogen fuel cell drone for rapid deployment of offshore charging, characterized by: The unmanned aerial vehicle body frame is provided with a hydrogen fuel cell assembly below, the hydrogen fuel cell assembly comprises a hydrogen fuel cell compartment and a hydrogen cylinder, the hydrogen fuel cell compartment is provided with a hydrogen cylinder mounting mechanism below, the hydrogen cylinder mounting mechanism comprises symmetrically arranged cylinder connecting arms, hollow cylinder fixing devices are arranged on both ends of the cylinder connecting arms, cylinder placing port covers are arranged on the cylinder fixing devices on both ends of the cylinder connecting arms on one side, the cylinder placing port covers are respectively hinged to both ends of the cylinder connecting arms on one side and are buckled to the cylinder fixing devices on the other side, and the unmanned aerial vehicle body frame is fixed to the outer surface of the cylinder fixing device. The unmanned aerial vehicle body frame comprises a control electrical compartment, arms, arm motors, a foot stand and a propeller, the arms are arranged at four corners of the control electrical compartment and are fixedly connected to the outer surface of the control electrical compartment at one end, the arm motors are arranged on the other end of the arms, the propeller is connected to the output end of the arm motor, the foot stand fixes the unmanned aerial vehicle body frame to the outer surface of the cylinder fixing device, the hydrogen fuel cell compartment is electrically connected to the control electrical compartment, and the hydrogen fuel cell compartment and the hydrogen cylinder are connected through an electrical comprehensive pipeline. The hydrogen fuel cell compartment and the control electrical compartment are electrically connected through a quick plug connector, the outer side of the hydrogen fuel cell compartment is provided with a fuel cell air inlet and a fuel cell air outlet, the hydrogen fuel cell compartment is provided with a storage battery, the storage battery is electrically connected to the output end of the hydrogen fuel cell compartment and is electrically connected to the control electrical compartment, the lower side of the hydrogen fuel cell compartment is provided with a charging mechanical arm, the end of the charging mechanical arm is provided with a charging interface, the charging interface is electrically connected to the storage battery, and the side of the hydrogen fuel cell compartment above the charging mechanical arm is provided with a visual positioning device.

2. A hydrogen fuel cell drone for rapid deployment offshore charging according to claim 1, characterized in that: The inside of the cylinder connecting arm is provided with an inwardly arranged first through groove, the inside of the first through groove is provided with a rotating shaft rotatably connected to the end of the cylinder connecting arm, one end of the rotating shaft is provided with a first belt pulley, the outside of the cylinder connecting arm above the first belt pulley is provided with a second through groove, the outside of the second through groove is provided with a rotating motor, the rotating motor is electrically connected to the control electrical compartment, the output end of the rotating motor is provided with a second belt pulley, the first belt pulley and the second belt pulley are provided with a driving belt, the rotating shaft arranged in the cylinder connecting arm is respectively wound with a traction rope and a floating water absorption soft plate, one end of the traction rope and the floating water absorption soft plate is fixed to the rotating shaft, and the other end of the traction rope and the floating water absorption soft plate is fixedly connected.

3. A hydrogen fuel cell drone for rapid deployment offshore charging according to claim 2, wherein: The floating water absorption soft plate comprises a waterproof bubble layer and a sponge layer, and the waterproof bubble layer is arranged above and is bonded to the sponge layer.

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