Integrated fuselage hydrogen fuel cell unmanned aerial vehicle

Abstract

The utility model discloses a hydrogen fuel cell unmanned aerial vehicle with an integrated vehicle body. The hydrogen fuel cell unmanned aerial vehicle comprises the vehicle body, vehicle arms, propellers, motors, a hydrogen fuel cell system, hydrogen cylinders, inverted-T-shaped foot stands and a cross beam. The machine body is of an integrated structure; the multiple vehicle arms are arranged around the vehicle body at equal angles, and the propellers and the motors are arranged at the tail ends of the vehicle arms. The hydrogen fuel cell system is arranged above the fuselage, and the hydrogen cylinder is hung below the fuselage; the two inverted-T-shaped foot stools are symmetrically arranged below the machine body, connected through a cross beam in the middle and used for fixing the hydrogen cylinder together. The hydrogen cylinders are arranged in an underneath mode, the fuselage is of an integrated structure, the space utilization rate of the unmanned aerial vehicle can be optimized, the flight performance of the unmanned aerial vehicle can be improved, the structure is compact, the weight is light, the endurance time is long, and the problem of endurance pain points in the prior art can be solved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to an integrated fuselage hydrogen fuel cell UAV. Background Technology

[0002] Most existing drones use lithium batteries as their power source, which suffers from problems such as short flight time, long charging time, and short lifespan. Fuel cells, as a new type of power source, have advantages such as high energy density and long flight time, which can effectively solve the industry pain points of short flight time and small payload in drones. However, the application of hydrogen fuel cells in drones is not yet widespread. Furthermore, existing hydrogen fuel cell drones suffer from structural design issues such as increased weight, poor signal shielding, and low internal space utilization, which limits their performance in practical applications.

[0003] Hydrogen fuel cells, as a novel power source, possess advantages such as high energy density, long flight time, and strong environmental adaptability. However, the application of fuel cells in drones still faces the following technical bottlenecks:

[0004] 1. Weight issue: The fuel cell system and its auxiliary equipment (such as hydrogen cylinders) are relatively heavy, which increases the overall weight of the drone and affects its flight performance.

[0005] 2. Layout optimization: The layout of fuel cells and gas cylinders directly affects the center of gravity distribution and flight stability of the drone.

[0006] 3. Structural Design: Existing UAV structural designs do not fully consider the integration requirements of fuel cell systems, resulting in problems such as low space utilization and high wind resistance.

[0007] 4. Poor signal shielding: Traditional metal fuselage structures may shield the communication signals of drones, affecting flight control and data transmission.

[0008] 5. Insufficient compatibility: Most existing drones use a single power source (such as lithium batteries or hydrogen fuel cells), making it difficult to flexibly switch power sources according to actual needs, which limits their application scope.

[0009] Therefore, there is an urgent need for a new type of drone fuselage structure design to solve the above-mentioned technical problems, give full play to the advantages of hydrogen fuel cells, and at the same time take into account the flexibility of lithium batteries. Utility Model Content

[0010] To address the aforementioned issues, this invention proposes an integrated fuselage hydrogen fuel cell drone, with the fuel cell cylinder positioned at the bottom and the fuselage being a single, integrated structure. This invention optimizes the space utilization of the drone, improves its flight performance, and features a compact structure, light weight, and long endurance, thus resolving the endurance bottleneck issue in existing technologies.

[0011] The technical solution adopted in this utility model is as follows:

[0012] An integrated hydrogen fuel cell drone includes a fuselage, arms, propellers, motors, a hydrogen fuel cell system, a hydrogen cylinder, inverted T-shaped landing gear, and a crossbeam. The fuselage is an integrated structure. Multiple arms are arranged at equal angles around the fuselage, with the propellers and motors located at the ends of the arms. The hydrogen fuel cell system is located above the fuselage, and the hydrogen cylinder is suspended below the fuselage. Two inverted T-shaped landing gears are symmetrically arranged below the fuselage, connected by a crossbeam, and together they secure the hydrogen cylinder.

[0013] Furthermore, the integrated hydrogen fuel cell drone also includes a fuel cell stack support and a first connector. The crossbeam and the inverted T-shaped legs are connected by slots. Screws pass through the slots and are locked to the first connector, so that the crossbeam automatically presses the hydrogen cylinder upward and in the center, while symmetrically locking the hydrogen cylinder with the fuel cell stack support.

[0014] Furthermore, the integrated fuselage hydrogen fuel cell drone also includes a second connector, which connects the fuselage and the hydrogen fuel cell system respectively, and the fuel cell stack of the hydrogen fuel cell system is fixed through the second connector.

[0015] Furthermore, the upper part of the second connector is provided with a slot, so that the screw can pass through the slot and be directly fixed to the end plates at both ends of the fuel cell stack.

[0016] Furthermore, the lower part of the second connector is configured to fit the arc shape of the gas cylinder, assisting in the installation and fixation of the gas cylinder.

[0017] Furthermore, the fuselage includes a lower fuselage plate and an upper fuselage plate, with an arm connecting the lower fuselage plate and the upper fuselage plate. The upper fuselage plate is connected to a hydrogen fuel cell system, and the lower fuselage plate is connected to a hydrogen cylinder and an inverted T-shaped support.

[0018] Furthermore, the lower panel of the fuselage is provided with several perforated holes.

[0019] Furthermore, a mounting hole is provided in the middle of the upper plate of the device, and the mounting hole matches the shape of the fuel cell stack of the hydrogen fuel cell system.

[0020] Furthermore, the lower fuselage plate and the upper fuselage plate are connected by hexagonal studs.

[0021] Furthermore, the hydrogen cylinder is connected to the anode inlet of the hydrogen fuel cell system via a pipeline to supply hydrogen to the fuel cell stack.

[0022] The beneficial effects of this utility model are as follows:

[0023] 1. Optimized center of gravity: By rationally arranging the fuel cell and hydrogen tank, the center of gravity distribution of the drone was optimized, improving flight stability and endurance.

[0024] 2. Robust structure: The fuselage is connected to the fuel cell system stack using connectors, ensuring the high strength and stability of the drone fuselage, effectively coping with various stresses during flight and extending the service life of the drone.

[0025] 3. Optimized space utilization: The optimized design of the lower and upper fuselage plates not only improves the utilization rate of internal space, but also reduces air resistance, further enhancing the flight performance and endurance of the drone.

[0026] 4. Strong compatibility: The design is compatible with both hydrogen fuel cells and lithium batteries, allowing for flexible selection of the power source according to actual needs. It can utilize the high energy density of hydrogen fuel cells to achieve long-range operation, or use lithium batteries in specific scenarios to simplify operation, significantly enhancing the applicability and flexibility of the drone.

[0027] 5. Easy installation: The snap-in design and connector design of the fuel cell make the installation and maintenance process simpler. Fuel cells can be installed and replaced without complicated tools, which greatly reduces the cost of use and maintenance.

[0028] 6. Easy to maintain: The layout and screw fastening of the hydrogen cylinder, as well as the detachable bracket and other structural designs, make it easy to replace and maintain the hydrogen cylinder. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the integrated fuselage hydrogen fuel cell drone of Embodiment 1 of this utility model; wherein, (a) is an isometric view of the drone and (b) is a right view of the drone.

[0030] Figure 2 This is a schematic diagram of the hydrogen cylinder fastening method in Embodiment 1 of this utility model.

[0031] Figure 3 This is a detailed schematic diagram of the hydrogen cylinder layout in Embodiment 1 of this utility model.

[0032] Figure 4 This is a schematic diagram of the beam structure of Embodiment 1 of this utility model; wherein, (a) is a top view of the beam and (b) is a front view of the beam.

[0033] Figure 5 This is a schematic diagram of the connection between the fuel cell stack and the second connector in Embodiment 1 of this utility model.

[0034] Figure 6 This is a schematic diagram of the integrated body of Embodiment 1 of this utility model.

[0035] Figure 7 This is a detailed structural diagram of the fuselage of Embodiment 1 of this utility model.

[0036] Reference numerals: 1-Lower fuselage plate, 2-Upper fuselage plate, 3-Arm, 4-Propeller, 5-Motor, 6-Hydrogen fuel cell system, 7-Hydrogen cylinder, 8-Inverted T-shaped bracket, 9-Crossbeam, 10-Stack support, 11-First connector, 12-Second connector, 13-Reinforcing member, 14-Hexagonal stud. Detailed Implementation

[0037] To provide a clearer understanding of the technical features, objectives, and effects of this utility model, specific embodiments are now described. It should be understood that the specific embodiments described herein are merely illustrative of this utility model and are not intended to limit it; that is, the described embodiments are only a part of, and not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without inventive effort are within the scope of protection of this utility model.

[0038] Example 1

[0039] like Figure 1 As shown, this embodiment provides an integrated fuselage hydrogen fuel cell drone, including a fuselage, arms 3, propellers 4, motors 5, a hydrogen fuel cell system 6, a hydrogen cylinder 7, inverted T-shaped landing gear 8, and a crossbeam 9; the fuselage is an integrated structure; multiple arms 3 are arranged at equal angles around the fuselage, and the propellers 4 and motors 5 are located at the ends of the arms 3 to provide lift for the drone; the hydrogen fuel cell system 6 is located above the fuselage, and the hydrogen cylinder 7 is suspended below the fuselage; there are two inverted T-shaped landing gear 8 symmetrically arranged below the fuselage, connected in the middle by the crossbeam 9, which together fix the hydrogen cylinder 7.

[0040] It should be noted that the hydrogen cylinder 7 is suspended under the fuselage, which ensures the overall stability of the drone and facilitates replacement and maintenance. The hydrogen cylinder 7 is connected to the anode inlet of the hydrogen fuel cell system 6 via pipeline, providing a stable supply of hydrogen to the fuel cell stack.

[0041] Preferably, the drone in this embodiment further includes a fuel cell stack support 10 and a first connector 11. For example... Figures 2-4 As shown, a slot is provided at the connection between the crossbeam 9 and the inverted T-shaped bracket 8. The crossbeam 9 automatically presses the hydrogen cylinder 7 upward and centered, and at the same time locks the hydrogen cylinder 7 symmetrically with the fuel cell stack bracket 10, so as to fix the hydrogen cylinder 7 and improve the stability of the machine body.

[0042] Preferably, the drone in this embodiment further includes a second connector 12. For example... Figure 5As shown, the second connector 12 connects the fuselage and the hydrogen fuel cell system 6 respectively, and the stack of the hydrogen fuel cell system 6 is fixed through the second connector 12.

[0043] More preferably, the upper part of the second connector 12 is provided with a slot, allowing screws to pass through the slot and be directly fixed to the end plates at both ends of the fuel cell stack; the lower part of the second connector 12 is designed with an arc shape to fit the gas cylinder, assisting in the installation and fixation of the gas cylinder. This connection structure not only strengthens the structural strength of the fuselage but also saves space, forming an integrated fuselage structure for the UAV.

[0044] like Figure 6 As shown, the fuselage in this embodiment is an integrated structure. Preferably, the fuselage includes a lower fuselage plate 1 and an upper fuselage plate 2. A robotic arm 3 connects the lower fuselage plate 1 and the upper fuselage plate 2, the upper fuselage plate 2 connects to a hydrogen fuel cell system 6, and the lower fuselage plate 1 connects to a hydrogen cylinder 7 and an inverted T-shaped support 8. The lower fuselage plate 1 and the upper fuselage plate 2 can be made of carbon fiber, which is lightweight and has high strength.

[0045] More preferably, the lower panel 1 of the fuselage is provided with several perforations, which not only reduces the overall weight of the UAV, but also reduces flow resistance, providing sufficient air for the electrochemical reaction and cooling of the air-cooled fuel cell.

[0046] More preferably, a mounting hole is provided in the middle of the upper plate 2 of the device body. The mounting hole matches the shape of the fuel cell stack of the hydrogen fuel cell system 6, making it convenient to put the fuel cell stack into it.

[0047] like Figure 7 As shown, reinforcing members 13 are added at locations with high stress on the lower fuselage plate 1 and the upper fuselage plate 2 to ensure the stability and compactness of the overall structure; the lower fuselage plate 1 and the upper fuselage plate 2 are connected by hexagonal studs 14.

[0048] Example 2

[0049] This embodiment provides an integrated fuselage hydrogen fuel cell drone, including a fuselage, arms 3, propellers 4, motors 5, a hydrogen fuel cell system 6, a hydrogen cylinder 7, an inverted T-shaped landing gear 8, a crossbeam 9, a fuel cell stack support 10, a first connector 11, a second connector 12, a reinforcing member 13, and a hexagonal stud 14, as detailed below.

[0050] In this embodiment, four arms 3 are provided. The four arms 3 are arranged at equal angles around the fuselage and connected to the fuselage. The ends of the arms 3 are equipped with motors 5 and propellers 4 to provide lift for the drone.

[0051] Preferably, the fuselage body is made of high-strength carbon fiber material, with key strength areas reinforced by reinforcing components 13 to ensure both lightweight and high strength. The main fuselage structure consists of a lower fuselage plate 1 and an upper fuselage plate 2, featuring light weight and high strength. The upper fuselage plate 2 has a hole in the middle that matches the shape of the air-cooled fuel cell in the hydrogen fuel cell system 6, facilitating the placement of the fuel cell. The lower fuselage plate 1 adopts a hollow perforated design, which reduces the overall weight of the drone and decreases flow resistance, providing sufficient air for the electrochemical reaction and cooling of the air-cooled fuel cell.

[0052] Preferably, the fuel cell of the hydrogen fuel cell system 6 is fixed to the body via a second connector 12. The upper part of the second connector 12 has a slotted hole to facilitate the screws to pass through and be directly fixed to the end plates at both ends of the air-cooled fuel cell. The lower part of the second connector 12 is connected to the lower plate 1 of the body via bolts.

[0053] Preferably, the lower part of the second connector 12 has an arc design, which can fit the hydrogen cylinder 7 and assist in the installation and fixation of the hydrogen cylinder 7. This connection structure not only strengthens the structural strength of the fuselage, but also saves space, forming an integrated fuselage structure for the drone.

[0054] Preferably, the lower fuselage plate 1 and the upper fuselage plate 2 are connected by hexagonal studs 14, making installation simple and quick. Reinforcing members 13 are added at locations of high stress on the lower fuselage plate 1 and the upper fuselage plate 2 to ensure the overall structural stability and compactness. This design is compatible with both hydrogen fuel cells and lithium batteries; the space for the fuel cell can help secure the lithium battery, allowing users to choose different power sources according to their actual needs, increasing the flexibility and applicability of the drone.

[0055] Preferably, the fuselage and the reinforcing member 13 are fixedly connected by bolts to ensure a stable and reliable connection. The reinforcing member 13 is mainly arranged in stress concentration areas of the fuselage, such as the connection of the arm 3 and the mounting point of the inverted T-shaped leg 8.

[0056] Preferably, the four robotic arms 3 are fixedly connected to the machine body by connectors and bolts, and installed around the machine body at equal angles (90° intervals) to ensure that the robotic arms 3 are evenly distributed.

[0057] In this embodiment, a motor 5 and a propeller are installed at the end of the arm 3. The motor 5 is fixed to the end of the arm 3 by bolts, and the propeller 4 is connected to the shaft of the motor 5 to ensure that the propeller 4 can provide stable lift.

[0058] In this embodiment, two detachable inverted T-shaped tripods 8 are symmetrically arranged under the fuselage to ensure that the tripods can support the drone and protect the hydrogen cylinder. The two inverted T-shaped tripods 8 are connected by a crossbeam 9, and the crossbeam 9 and the inverted T-shaped tripods 8 are fixedly connected by a first connector 11 and bolts to ensure the stability of the overall structure.

[0059] In this embodiment, the hydrogen fuel cell system 6 is mounted on the upper part of the fuselage, ensuring its position is close to the center of gravity of the drone to optimize the center of gravity distribution. An aluminum alloy stack bracket 10 can be used to fix the hydrogen fuel cell system 6 stack to the fuselage. The stack bracket 10 is connected to the end plates on both sides of the stack and the fuselage by bolts to ensure the stability of the stack.

[0060] In this embodiment, the hydrogen cylinder 7 is suspended below the fuselage, ensuring its symmetrical distribution to maintain the overall stability of the drone's center of gravity. Fixing method: A crossbeam 9 connects two inverted T-shaped legs 8. An elongated slot is made at the connection point between the crossbeam 9 and the inverted T-shaped legs 8. Screws pass through the slot and are locked to the first connecting piece 11, causing the crossbeam 9 to automatically press the hydrogen cylinder 7 upwards and center it, while simultaneously symmetrically locking the cylinder 7 to the fuel cell stack support 10.

[0061] Through the above specific embodiments, this utility model provides an integrated fuselage design for a quadcopter hydrogen fuel cell drone that is structurally robust, easy to install, and highly compatible. The connecting structure not only strengthens the structural strength of the carbon fiber sheet fuselage but also saves space, forming an integrated fuselage structure for the drone. This effectively solves the problems in the prior art, improves the performance and application range of the drone, and achieves the design goals of lightweight, high stability, and long endurance, while also offering advantages such as ease of maintenance and operation.

[0062] The above description is merely a preferred embodiment of this utility model. It should be understood that this utility model is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the concept described herein through the above teachings or the technology or knowledge in related fields. Modifications and variations made by those skilled in the art that do not depart from the spirit and scope of this utility model should be protected within the scope of the appended claims. Furthermore, the terms "first," "second," "third," etc., are used only for distinguishing descriptions and should not be construed as indicating or implying relative importance.

Claims

1. An integrated airframe hydrogen fuel cell drone, characterized by, The system includes a fuselage, arms (3), propellers (4), motors (5), a hydrogen fuel cell system (6), a hydrogen cylinder (7), inverted T-shaped legs (8), and a crossbeam (9). The fuselage is an integrated structure. There are multiple arms (3) arranged at equal angles around the fuselage. The propellers (4) and motors (5) are located at the ends of the arms (3). The hydrogen fuel cell system (6) is located above the fuselage, and the hydrogen cylinder (7) is suspended below the fuselage. There are two inverted T-shaped legs (8) arranged symmetrically below the fuselage. They are connected by a crossbeam (9) and together they fix the hydrogen cylinder (7).

2. The unmanned aerial vehicle of claim 1, wherein, It also includes a fuel cell stack support (10) and a first connector (11). The crossbeam (9) is provided with a slot at the connection between it and the inverted T-shaped bracket (8). The crossbeam (9) is locked to the first connector (11) by passing screws through the slots, so that the crossbeam (9) automatically presses the hydrogen cylinder (7) upward and centered, and at the same time locks the hydrogen cylinder (7) symmetrically with the fuel cell stack support (10).

3. The unmanned aerial vehicle of claim 1, wherein, It also includes a second connector (12), which connects the fuselage and the hydrogen fuel cell system (6) respectively, and the stack of the hydrogen fuel cell system (6) is fixed by the second connector (12).

4. The one-piece body hydrogen fuel cell drone of claim 3, wherein, The second connector (12) has a slot on its upper part, which allows the screw to pass through the slot and be directly fixed to the end plates at both ends of the fuel cell stack.

5. The one-body hydrogen fuel cell drone of claim 3, wherein, The lower part of the second connector (12) is set to fit the arc shape of the gas cylinder to assist in the installation and fixation of the gas cylinder.

6. The one-body hydrogen fuel cell drone of claim 1, wherein, The fuselage includes a lower fuselage plate (1) and an upper fuselage plate (2), with a boom (3) connected between the lower fuselage plate (1) and the upper fuselage plate (2). The upper fuselage plate (2) is connected to a hydrogen fuel cell system (6), and the lower fuselage plate (1) is connected to a hydrogen cylinder (7) and an inverted T-shaped bracket (8).

7. The one-body hydrogen fuel cell drone of claim 6, wherein, The lower panel (1) of the fuselage is provided with several perforated holes.

8. The one-body hydrogen fuel cell drone of claim 6, wherein, A mounting hole is provided in the middle of the upper plate (2) of the fuselage, and the mounting hole matches the shape of the fuel cell stack of the hydrogen fuel cell system (6).

9. The one-body hydrogen fuel cell drone of claim 6, wherein, The lower fuselage plate (1) and the upper fuselage plate (2) are connected by hexagonal studs (14).

10. The one-body hydrogen fuel cell drone of claim 1, wherein, The hydrogen cylinder (7) is connected to the anode inlet of the hydrogen fuel cell system (6) via a pipeline to provide hydrogen supply to the fuel cell stack.

Images