A modular hydrogen-powered drone

Abstract

The present invention proposes a modular hydrogen-powered drone, which relates to the field of drones. The drone includes a main body, a power module, and a hydrogen fuel supply module. The main body is evenly arranged with multiple rotorcraft main arms, and the multiple rotorcraft main arms are commonly connected to a landing gear. The power module includes rotorcraft external force arms of the same number as the rotorcraft main arms. The multiple rotorcraft external force arms are detachably mounted on the outer ends of the multiple rotorcraft main arms, and any rotorcraft external force arm is provided with a take-off and landing rotor module. The hydrogen fuel supply module includes a hydrogen fuel cell module and a hydrogen cylinder mounted on the main body. Both the hydrogen cylinder and the hydrogen fuel cell are detachably mounted on the main body. The hydrogen fuel cell and the take-off and landing rotor module, as well as the hydrogen fuel cell and the main body, are detachably electrically connected via wire connectors. In the present invention, the modular splicing design increases the scope of use, and the hydrogen fuel cell design has the advantages of long flight time and environmental protection.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a modular hydrogen-powered UAV. Background Art

[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aircraft controlled by radio remote control and self-contained programmable controls. They lack a cockpit but are equipped with an autopilot, programmable controls, and other equipment. Personnel on the ground, on a ship, or at the remote control station behind the aircraft use radar and other equipment to track, locate, remotely control, telemeter, and transmit data. They can take off like conventional aircraft or be launched with booster rockets under radio remote control, or they can be carried and released from a mother aircraft. Recovery can occur automatically, similar to the landing process of a conventional aircraft, or by remote control using a parachute or a net. They can be used repeatedly.

[0003] The main shortcomings of the currently used drones are as follows:

[0004] First, most drones use lithium batteries or fuel as energy. Lithium batteries have a relatively short battery life, while fuel will cause certain pollution to the environment during use, which is not environmentally friendly.

[0005] 2. Most drones have an integrated structure. Drones of different specifications and models have different ranges and power systems. Drones of different specifications and models can only be used in specific scenarios, and their scope of use is relatively limited.

[0006] In summary, we proposed a modular hydrogen-powered UAV to solve the above technical problems. Summary of the Invention

[0007] The purpose of the present invention is to provide a modular hydrogen energy drone. The modular splicing design increases the scope of use, and the hydrogen fuel cell design has the advantages of long flight time and environmental protection.

[0008] The embodiment of the present invention is achieved as follows:

[0009] The embodiment of the present application provides a modular hydrogen-powered drone, comprising a main body, a power module, and a hydrogen fuel supply module;

[0010] A plurality of rotorcraft main arms are evenly arranged around the main fuselage, and the plurality of rotorcraft main arms are commonly connected to a landing gear;

[0011] The power module includes a rotorcraft external force arm having the same number as the rotorcraft main force arm, and the plurality of the rotorcraft external force arms are detachably mounted on the outer ends of the plurality of the rotorcraft main force arms, and any of the rotorcraft external force arms is provided with a take-off and landing rotor module;

[0012] The above-mentioned hydrogen fuel energy supply module includes a hydrogen fuel cell module arranged on the above-mentioned main body, and a hydrogen cylinder for transporting hydrogen to the above-mentioned hydrogen fuel cell module. The above-mentioned hydrogen cylinder and the above-mentioned hydrogen fuel cell can be detachably arranged on the above-mentioned main body. The above-mentioned hydrogen fuel cell and the above-mentioned take-off and landing rotor module, and the above-mentioned hydrogen fuel cell and the above-mentioned main body are all detachably electrically connected through wire connectors.

[0013] In some embodiments of the present invention, an arm connector is further included, wherein the arm connector has three connecting parts, one of which is detachably arranged at the outer end of the main arm of the rotorcraft, and the other two connecting parts of the arm connector are provided with the power module.

[0014] In some embodiments of the present invention, the take-off and landing rotor module includes a drive motor disposed on an upper side of the rotorcraft outer lever arm, and an output shaft of the drive motor is provided with a rotor member.

[0015] In some embodiments of the present invention, the above-mentioned arm connecting member, the above-mentioned rotorcraft external force arm and the above-mentioned rotorcraft main arm are all hollow structures, and the wires connecting the above-mentioned drive motor to the above-mentioned hydrogen fuel cell are arranged in the above-mentioned rotorcraft external force arm, the above-mentioned arm connecting member and the above-mentioned rotorcraft main arm.

[0016] In some embodiments of the present invention, the hydrogen cylinder is arranged on the upper side of the main body, the hydrogen fuel cell is arranged behind the lower side of the main body, and a connection hole for an external load module is opened in the front of the lower side of the main body.

[0017] In some embodiments of the present invention, the hydrogen cylinder is connected to the main body via a clamp.

[0018] In some embodiments of the present invention, slots are symmetrically provided on the bottom side of the main body, and the hydrogen fuel cell module is provided with inserts that are plugged into the slots.

[0019] Compared with the prior art, the embodiments of the present invention have at least the following advantages or beneficial effects:

[0020] (1) The detachable setting of the hydrogen cylinder allows the replacement of hydrogen cylinders of different capacities according to different flight time requirements, which has the advantages of being able to fly for a long flight time and replace small hydrogen cylinders for short flight time and lightweight flight; the detachable setting of the hydrogen fuel cell allows the replacement of hydrogen fuel cells of different output power according to the different power requirements of the UAV; the detachable setting of the power module allows the replacement of different power systems according to the different mission requirements of the aircraft, which is more flexible. In the present invention, the hydrogen cylinder, hydrogen fuel cell and power module are all designed with modular splicing with the main body. According to the flight mission requirements, the modules (hydrogen cylinder, hydrogen fuel cell and power module) that better match the flight mission can be selected as much as possible to achieve the overall optimized ratio of the UAV, forming UAVs with different performances and a wider range of uses.

[0021] (2) In the present invention, hydrogen fuel cells are used as the main energy source, which has a longer flight time than ordinary lithium battery aircraft and is more environmentally friendly than diesel aircraft.

[0022] (3) The wires for connecting the drive motor to the hydrogen fuel cell are arranged inside the rotorcraft outer arm, the arm connector, and the rotorcraft main arm, so that the wires are arranged in a hidden manner, which is more reasonable and practical. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments. It should be understood that the following drawings only illustrate certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying any creative work.

[0024] Figure 1 This is a schematic structural diagram of a modular hydrogen-powered drone according to an embodiment of the present invention;

[0025] Figure 2 This is a schematic structural diagram of a main body according to an embodiment of the present invention;

[0026] Figure 3 This is a structural diagram of a storage bin according to an embodiment of the present invention;

[0027] Figure 4 Schematic diagram of the structure of the arm connecting member according to an embodiment of the present invention.

[0028] Icons: 1-landing gear, 2-hydrogen fuel cell, 3-storage compartment, 4-rotor component, 5-drive motor, 6-rotorcraft external force arm, 7-hydrogen cylinder, 8-rotorcraft main arm, 9-main body, 10-clamp, 11-slot, 12-insert, 13-arm connector, 14-nut, 15-external thread. DETAILED DESCRIPTION

[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0030] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention.

[0031] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0032] In the description of the embodiments of the present invention, it should be noted that if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the accompanying drawings, or the orientation or position relationship in which the product of the invention is usually placed when in use. It is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, it should not be understood as limiting the present invention. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description and should not be understood as indicating or implying relative importance.

[0033] Furthermore, the use of terms such as "horizontal," "vertical," and "overhanging" does not necessarily imply that the component must be absolutely horizontal or overhanging, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," not that the structure must be completely horizontal, but rather that it can be slightly tilted.

[0034] In the description of the embodiments of the present invention, "a plurality of" means at least two.

[0035] In the description of the embodiments of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0036] Example

[0037] Please refer to Figures 1-4 , this embodiment provides a modular hydrogen energy UAV, including a main body 9, a power module and a hydrogen fuel energy supply module;

[0038] The main body 9 is evenly arranged with a plurality of rotorcraft main arms 8 in the circumferential direction, and the plurality of rotorcraft main arms 8 are commonly connected to the landing gear 1;

[0039] The power module includes a rotorcraft external force arm 6 having the same number as the rotorcraft main force arm 8, and the plurality of rotorcraft external force arms 6 are detachably mounted on the outer ends of the plurality of rotorcraft main force arms 8, and any of the rotorcraft external force arms 6 is provided with a take-off and landing rotor module;

[0040] The above-mentioned hydrogen fuel energy supply module includes a hydrogen fuel cell 2 module arranged on the above-mentioned main fuselage 9, and a hydrogen cylinder 7 for transporting hydrogen to the above-mentioned hydrogen fuel cell 2 module. The above-mentioned hydrogen cylinder 7 and the above-mentioned hydrogen fuel cell 2 can be detachably arranged on the above-mentioned main fuselage 9. The above-mentioned hydrogen fuel cell 2 and the above-mentioned take-off and landing rotor module, and the above-mentioned hydrogen fuel cell 2 and the above-mentioned main fuselage 9 are all detachably electrically connected through wire connectors.

[0041] First, the removable hydrogen cylinder 7 allows for replacement of different capacity hydrogen cylinders 7 according to flight duration requirements, offering the advantages of both long-duration flight and shorter, lightweight flight with smaller hydrogen cylinders 7. The removable hydrogen fuel cell 2 allows for replacement of hydrogen fuel cells 2 with different output powers according to the drone's varying power requirements. The removable power module allows for replacement of different power systems according to the aircraft's varying mission requirements, providing greater flexibility. In the present invention, the hydrogen cylinder 7, hydrogen fuel cell 2, and power module all utilize a modular design with the main fuselage 9. Based on the flight mission requirements, the modules (hydrogen cylinder 7, hydrogen fuel cell 2, and power module) that best match the mission can be selected to achieve an optimized overall configuration for the drone, creating drones with varying performance and a wider range of applications. Second, the present invention utilizes a hydrogen fuel cell 2 as the primary energy source, resulting in a longer flight time than conventional lithium-ion battery aircraft and a more environmentally friendly design compared to diesel aircraft.

[0042] The hydrogen cylinder 7 and the hydrogen fuel cell 2 are connected via a quick connector to facilitate replacement of the hydrogen fuel cell 2 or the hydrogen cylinder 7 .

[0043] In some embodiments of the present invention, an arm connector 13 is further included, and the arm connector 13 has three connecting parts. One of the connecting parts of the arm connector 13 is detachably arranged on the outer end of the main arm 8 of the rotorcraft, and the other two connecting parts of the arm connector 13 are provided with the power module.

[0044] In the above embodiment, the three connecting parts are evenly spaced along the same circumference, the connecting part connected to the rotorcraft main force arm 8 is connected by rivets, the rotorcraft external force arm 6 of the power module is provided with a nut 14, and the connecting part is provided with an external thread 15 that cooperates with the thread of the nut 14 to realize a detachable connection between the rotorcraft external force arm 6 and the connecting part.

[0045] In some embodiments of the present invention, the take-off and landing rotor module includes a drive motor 5 disposed on the upper side of the rotorcraft outer lever 6 , and the output shaft of the drive motor 5 is provided with a rotor member 4 .

[0046] In the above embodiment, the drive motor 5 drives the rotor 4 to rotate, providing lift for the drone to take off and land. As a power source, the drive motor 5 has the advantage of stable power output.

[0047] In some embodiments of the present invention, the above-mentioned arm connecting member 13, the above-mentioned rotorcraft external force arm 6 and the above-mentioned rotorcraft main arm 8 are all hollow structures, and the wires connecting the above-mentioned drive motor 5 to the above-mentioned hydrogen fuel cell 2 are arranged in the above-mentioned rotorcraft external force arm 6, the above-mentioned arm connecting member 13 and the above-mentioned rotorcraft main arm 8.

[0048] In the above embodiment, the hollow tube of the rotorcraft outer arm 6 is inserted into the connecting part, and then threadedly connected through the nut 14 and the external thread 15 of the connecting part. The wires of the drive motor 5 are passed through the hollow structure of the rotorcraft outer arm 6, the arm connector 13 and the rotorcraft main arm 8, and the wire connector is located at the junction of the connecting part and the rotorcraft outer arm 6 to facilitate the connection of the wires.

[0049] In some embodiments of the present invention, the hydrogen cylinder 7 is arranged on the upper side of the main body 9, the hydrogen fuel cell 2 is arranged behind the lower side of the main body 9, and a connection hole for an external load module is opened in the front of the lower side of the main body 9.

[0050] In the above embodiment, the external load module may be a cargo compartment, and the cargo compartment may be detachably mounted on the connection hole by bolts to achieve replacement of the external load module to meet different cargo requirements.

[0051] In some embodiments of the present invention, the hydrogen cylinder 7 is connected to the main body 9 via a clamp 10 .

[0052] In the above embodiment, the design of the clamp 10 connects the hydrogen cylinder 7 and the main body 9 together, and enables the hydrogen cylinder 7 to be detachable, so that the replacement of the hydrogen cylinder 7 is convenient.

[0053] In some embodiments of the present invention, a slot 11 is symmetrically provided on the bottom side of the main body 9 , and the hydrogen fuel cell 2 module is provided with an insert 12 that plugs into and cooperates with the slot 11 .

[0054] In the above embodiment, the hydrogen fuel cell module 2 includes a storage compartment 3, into which the hydrogen fuel cell 2 can be removably placed. Inserts 12 are arranged on either side of the storage compartment 3, and the two inserts 12 respectively engage with the two slots 11 to achieve a removable connection between the hydrogen fuel cell 2 and the main body 9. The main body 9 and the storage compartment 3 can be positioned by rotating a rotary card or by screws (both the main body 9 and the storage compartment 3 have screw holes, which are butted together and connected by screws to achieve a removable connection between the storage compartment 3 and the main body 9).

[0055] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A modular hydrogen-powered drone, characterized in that: It includes the main body, power module and hydrogen fuel supply module; A plurality of rotorcraft main arms are evenly arranged around the main fuselage, and the plurality of rotorcraft main arms are commonly connected to a landing gear; The power module includes a number of rotorcraft external force arms equal to the number of the rotorcraft main arms, and the plurality of rotorcraft external force arms are detachably arranged at the outer ends of the plurality of rotorcraft main arms, and any of the rotorcraft external force arms is provided with a take-off and landing rotor module; The hydrogen fuel energy supply module includes a hydrogen fuel cell module arranged on the main fuselage, and a hydrogen cylinder for supplying hydrogen to the hydrogen fuel cell module. The hydrogen cylinder and the hydrogen fuel cell can be detachably arranged on the main fuselage. The hydrogen fuel cell and the take-off and landing rotor module, and the hydrogen fuel cell and the main fuselage are detachably electrically connected via wire connectors; the hydrogen cylinder and the hydrogen fuel cell are connected via quick connectors; and an arm connector is also included, the arm connector having three connecting parts, one of which is detachably arranged on the outer end of the main arm of the rotorcraft, and the The power module is set at the other two connecting parts of the arm connecting piece; the arm connecting piece, the rotorcraft outer force arm and the rotorcraft main arm are all hollow structures, the take-off and landing rotor module includes a drive motor arranged on the upper side of the rotorcraft outer force arm, the output shaft of the drive motor is provided with a rotor part, and the wires connecting the drive motor to the hydrogen fuel cell are arranged in the rotorcraft outer force arm, the arm connecting piece and the rotorcraft main arm; according to the flight mission requirements, hydrogen cylinders, hydrogen fuel cells and power modules that better match the flight mission are selected to achieve an optimized ratio of the entire drone and form drones with different performances.

2. A modular hydrogen-powered UAV according to claim 1, characterized in that: The hydrogen cylinder is arranged on the upper side of the main body, the hydrogen fuel cell is arranged at the rear of the lower side of the main body, and a connection hole for an external load module is opened at the front of the lower side of the main body.

3. A modular hydrogen-powered UAV according to claim 1, characterized in that: The hydrogen cylinder is connected to the main body via a clamp.

4. A modular hydrogen-powered UAV according to claim 1, characterized in that: Slots are symmetrically provided on the bottom side of the main body, and the hydrogen fuel cell module is provided with inserting strips that are plugged into and matched with the slots.

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