Hydrogen-powered double-fuselage vertical take-off and landing fixed-wing unmanned aerial vehicle

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a hydrogen-powered double-fuselage vertical take-off and landing fixed-wing unmanned aerial vehicle which comprises an unmanned aerial vehicle body, a power energy system and a landing device, the unmanned aerial vehicle body comprises two fuselages, wings, empennages and a mounting cabin, the two fuselages are symmetrically arranged at the bottoms of the wings, and rotor wing assemblies and tail thrust assemblies are arranged on the fuselages; the power energy system is arranged in the fuselage, the landing device is arranged at the bottom of the fuselage, the power energy system comprises a hydrogen cylinder, a hydrogen fuel cell and a storage battery, the hydrogen cylinder is connected with the hydrogen fuel cell and used for providing hydrogen for the hydrogen fuel cell to generate electric energy, the hydrogen fuel cell is connected with the tail thrust assembly, and the storage battery is connected with the rotor wing assembly. According to the invention, the two fuselages and the mounting cabin are arranged, the fuselages and the carrying space are separately arranged, and the hydrogen fuel cells are arranged in the two fuselages, so that not only is the independent transportation space provided, but also the longer cruising ability is provided, and the transportation efficiency is greatly improved.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically a hydrogen-powered, twin-fuselage, vertical take-off and landing (VTOL) fixed-wing UAV. Background Technology

[0002] Hydrogen-powered drones are unmanned aerial vehicles that use hydrogen fuel cells as their core power source, generating electricity through the chemical reaction of hydrogen and oxygen. These drones feature zero carbon emissions, ultra-long endurance, and low-temperature resistance, and are primarily used in fields such as power transmission line inspection, high-altitude surveying, and emergency communications. To enhance the adaptability of drones to different mission scenarios and eliminate the limitations of traditional runways, vertical take-off and landing (VTOL) fixed-wing drones have been developed for hydrogen-powered drones. However, existing hydrogen-powered VTOL fixed-wing drones consist of only a fuselage, with the hydrogen tank and fuel cell fixed inside. This significantly reduces the cargo space, limiting transport to small quantities and multiple trips, resulting in low transport efficiency. Summary of the Invention

[0003] To address the problems mentioned above, this invention provides a hydrogen-powered dual-fuselage vertical takeoff and landing fixed-wing UAV, which features two fuselages and a payload bay, separating the fuselage and transport space. Both fuselages are equipped with hydrogen fuel cells, providing not only independent transport space but also longer endurance and significantly improving transport efficiency.

[0004] This invention provides a hydrogen-powered dual-fuselage vertical takeoff and landing (VTOL) fixed-wing unmanned aerial vehicle (UAV), comprising a UAV body, a power system, and a landing gear. The UAV body includes two fuselages, wings, a tail fin, and a payload bay. The two fuselages are symmetrically arranged at the bottom of the wings, the tail fin is located between the tails of the two fuselages, and the payload bay is located at the bottom of the wings and between the two fuselages. A rotor assembly and a tail thrust assembly are arranged on the fuselages. The power system is located inside the fuselage, and the landing gear is located at the bottom of the fuselage. The power system includes a hydrogen cylinder, a hydrogen fuel cell, and a battery. The hydrogen cylinder is connected to the hydrogen fuel cell to provide hydrogen to the hydrogen fuel cell to generate electricity. The hydrogen fuel cell is connected to the tail thrust assembly, and the battery is connected to the rotor assembly.

[0005] Furthermore, the fuselage has a long, slender, streamlined circular cross-section, the wings are high-aspect-ratio single straight wings, and the tail is an inverted V-shape.

[0006] Furthermore, ailerons are provided on both trailing edges of the wings, and a first servo motor is connected to the aileron. The first servo motor controls the aileron to swing, so as to change the attitude of the main body of the UAV.

[0007] Furthermore, there are two ailerons on each side of the wing, and each aileron on each side has a first servo motor. Each first servo motor controls one aileron and is powered independently.

[0008] Furthermore, control surfaces are provided on both trailing edges of the tail fin, and second servo motors are connected to the control surfaces. The second servo motors control the swing of the control surfaces to achieve pitch and small-angle turning of the UAV body. There are two control surfaces on each side of the tail fin, and each of the two control surfaces on each side has a second servo motor. Each servo motor controls one control surface and is powered independently.

[0009] Furthermore, the rotor assembly is provided in four sets, which are respectively located at the front and rear ends of the two fuselages. The rotor assembly includes a rotor propeller and a first drive motor. The first drive motor is fixed to the bottom of the fuselage and is connected to the battery. The rotor propeller is mounted on the output shaft of the first drive motor. The first drive motor drives the rotor propeller to rotate, so as to realize the vertical take-off and landing of the UAV body.

[0010] Furthermore, there are two sets of tail thrust assemblies, which are respectively located at the tail of the two fuselages. Each tail thrust assembly includes a tail thrust propeller and a second drive motor. The second drive motor is fixed at the tail of the fuselage and is connected to the hydrogen fuel cell. The tail thrust propeller is mounted on the output shaft of the second drive motor. The second drive motor drives the tail thrust propeller to rotate, thereby enabling the drone to cruise.

[0011] Furthermore, each fuselage has an air inlet on its top, located above the hydrogen fuel cell.

[0012] Furthermore, each unit is equipped with a cooling fan at the bottom, located below the hydrogen fuel cell.

[0013] Furthermore, the landing gear includes two landing gears, each located at the bottom of one of the fuselages.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0015] (1) The present invention is provided with two fuselages and one load compartment, that is, the space for loading hydrogen cylinders and hydrogen fuel cells and the space for transportation are set separately. Each fuselage is equipped with hydrogen cylinders and hydrogen fuel cells. It not only has independent transportation space, which can transport more items, but also has a longer endurance, which improves the endurance and range, and greatly improves transportation efficiency and carrying capacity.

[0016] (2) The main body of the UAV adopts an aerodynamic layout design of "circular cross-section slender streamlined fuselage + high aspect ratio single straight wing + inverted V-shaped tail", which not only reduces air resistance, but also improves the lift-to-drag ratio of the whole aircraft. During the cruise phase, it can effectively reduce cruise power and improve endurance and range.

[0017] (3) Two ailerons and control surfaces are provided on each side, and each is controlled by an independent servo. This achieves a dual-backup design for the ailerons and control surfaces. When one of them on one side fails and cannot move, the other on the same side can continue to work without being affected by the failure. This greatly reduces the possibility of the UAV becoming unbalanced and ensures the safe operation of the UAV. Similarly, the two tail thrusters at the tail of the two fuselages are also independent of each other. Even if a single engine fails, the forward propulsion of the UAV can still be guaranteed, thus ensuring the safe operation of the UAV. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 A schematic diagram of the overall structure of a hydrogen-powered, twin-fuselage, vertical takeoff and landing (VTOL) fixed-wing unmanned aerial vehicle (UAV).

[0020] Figure 2 This is a schematic diagram of the internal structure of the fuselage;

[0021] Explanation of reference numerals in the attached drawings: 1. Fuselage; 2. Wing; 3. Tail; 4. Utility bay; 5. Rotor assembly; 50. Rotor propeller; 51. First drive motor; 6. Tail thrust assembly; 60. Tail thrust propeller; 61. Second drive motor; 7. Hydrogen tank; 8. Hydrogen fuel cell; 9. Aileron; 10. Control surfaces; 11. Air intake; 12. Cooling fan; 13. Landing gear. Detailed Implementation

[0022] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present invention.

[0023] The following is in conjunction with the appendix Figure 1 To be continued Figure 2The invention is described in detail with specific embodiments.

[0024] Reference Figures 1-2 This invention provides a hydrogen-powered dual-fuselage vertical take-off and landing fixed-wing unmanned aerial vehicle (UAV), comprising a UAV body, a power energy system, and a landing device. The UAV body includes two fuselages 1, wings 2, a tail 3, and a payload bay 4. The two fuselages 1 are symmetrically arranged at the bottom of the wings 2. The tail 3 is located between the tails of the two fuselages 1. The payload bay 4 is located at the bottom of the wings 2 and between the two fuselages 1. A rotor assembly 5 and a tail thrust assembly 6 are provided on the fuselage 1. The power energy system is located inside the fuselage 1, and the landing device is located at the bottom of the fuselage 1. The power energy system includes a hydrogen cylinder 7, a hydrogen fuel cell 8, and a battery. The hydrogen cylinder 7 is connected to the hydrogen fuel cell 8 to provide hydrogen to the hydrogen fuel cell 8 to generate electricity. The hydrogen fuel cell 8 is connected to the tail thrust assembly 6, and the battery is connected to the rotor assembly 5.

[0025] The present invention is provided with two fuselages 1 and one payload compartment 4, that is, the space for loading hydrogen cylinders 7 and hydrogen fuel cells 8 is set separately from the space for transportation. Each fuselage 1 is provided with hydrogen cylinders 7 and hydrogen fuel cells 8. It not only has independent transportation space, which can transport more goods, but also has a longer endurance, which improves the endurance and range, and greatly improves transportation efficiency and carrying capacity.

[0026] This invention also features two flight modes: rotorcraft mode and fixed-wing mode. In fixed-wing mode, it can cruise and fly rapidly forward with high maneuverability. In rotorcraft mode, it can also achieve vertical takeoff and landing (VTOL) and hovering. Compared to conventional fixed-wing UAVs, it is freed from the limitations of traditional runways, has lower requirements for takeoff and landing site conditions, and possesses stronger adaptability to various mission scenarios. Specifically, during VTOL, the rotor assembly 5 provides lift and achieves attitude control. After climbing to a safe and stable altitude, it transitions to cruise level flight, where the tail thrust assembly 6 provides forward propulsion, and the lift from the wings 2 gradually replaces the lift provided by the rotor assembly 5. After the flight mission is completed, it switches back from fixed-wing mode to rotorcraft mode, reaches above the landing point, and completes a stationary vertical landing.

[0027] The fuselage 1 is a long and slender streamlined shape with a circular cross-section, the wing 2 is a single straight wing with a high aspect ratio, and the tail 3 is an inverted V-shape. The main body of the UAV adopts an aerodynamic layout design of "funnel 1 with a long and slender streamlined shape with a circular cross-section + wing 2 with a single straight wing with a high aspect ratio + inverted V-shaped tail 3", which not only reduces air resistance but also improves the lift-to-drag ratio of the entire aircraft. During the cruise phase, it can effectively reduce cruise power and improve endurance and range.

[0028] Ailerons 9 are located on the trailing edges of both sides of wing 2. A first servo motor is connected to the aileron 9. The first servo motor controls the swing of the aileron 9 to change the attitude of the UAV body. There are two ailerons 9 on each side of wing 2. Each aileron 9 on each side is equipped with a first servo motor. Each first servo motor controls one aileron 9 independently and is powered by a battery.

[0029] Both sides of the tail 3 are provided with control surfaces 10. The control surfaces 10 are connected to second servo motors. The second servo motors control the swing of the control surfaces 10 to achieve pitch and small-angle turning of the UAV body. There are two control surfaces 10 on each side of the tail 3. Each of the two control surfaces 10 on each side is equipped with a second servo motor. Each servo motor controls one control surface 10 and is independently powered by a battery.

[0030] Each side has two ailerons 9 and control surfaces 10, each controlled by an independent servo. This dual-backup design ensures that if one aileron 9 or control surface 10 malfunctions, the other on the same side can continue operating unaffected by the failure, significantly reducing the likelihood of the UAV becoming unbalanced and guaranteeing its safe operation. Similarly, the two tail thrusters 6 at the rear of the two fuselages 1 are also independent, maintaining forward propulsion even in the event of a single engine failure, thus ensuring the UAV's safe operation.

[0031] The rotor assembly 5 is provided in four sets, which are respectively located at the front and rear ends of the two fuselages 1. The rotor assembly 5 includes a rotor propeller 50 and a first drive motor 51. The first drive motor 51 is fixed to the bottom of the fuselage 1 and is connected to the battery. The rotor propeller 50 is mounted on the output shaft of the first drive motor 51. The first drive motor 51 drives the rotor propeller 50 to rotate, so as to realize the vertical take-off and landing of the UAV body.

[0032] Two sets of tail thrust assemblies 6 are provided, and the two sets of tail thrust assemblies 6 are respectively located at the tail of the two fuselages 1. The tail thrust assembly 6 includes a tail thrust propeller 60 and a second drive motor 61. The second drive motor 61 is fixed at the tail of the fuselage 1 and is connected to the hydrogen fuel cell 8. The tail thrust propeller 60 is mounted on the output shaft of the second drive motor 61. The second drive motor 61 drives the tail thrust propeller 60 to rotate, so as to realize the cruise of the UAV body.

[0033] Each unit 1 has an air inlet 11 on its top. The air inlet 11 is located above the hydrogen fuel cell 8. The air inlet 11 can not only provide oxygen to the hydrogen fuel cell 8, but also provide air cooling for the hydrogen fuel cell 8.

[0034] Each unit 1 is equipped with a cooling fan 12 at its bottom. The cooling fan 12 is located below the hydrogen fuel cell 8 and mainly serves to dissipate heat from the hydrogen fuel cell 8, thereby ensuring the normal operation of the hydrogen fuel cell 8.

[0035] The landing gear includes two landing gears 13, which are located at the bottom of the two fuselages 1 respectively. The landing gears 13 mainly support the main body of the UAV and ensure the safe landing of the UAV.

[0036] The present invention has been further described above with reference to specific embodiments. However, it should be understood that the specific description herein should not be construed as limiting the nature and scope of the present invention. Various modifications made to the above embodiments by those skilled in the art after reading this specification are all within the scope of protection of the present invention.

Claims

1. A hydrogen-powered, twin-fuselage, vertical takeoff and landing (VTOL) fixed-wing unmanned aerial vehicle (UAV), characterized in that, The device includes a drone body, a power system, and a landing device. The drone body includes two fuselages (1), wings (2), a tail fin (3), and a payload bay (4). The two fuselages (1) are symmetrically arranged at the bottom of the wings (2). The tail fin (3) is located between the tails of the two fuselages (1). The payload bay (4) is located at the bottom of the wings (2) and between the two fuselages (1). The fuselages (1) are equipped with rotor assembly (5) and tail thrust assembly (6). The power system is located inside the fuselages (1). The landing device is located at the bottom of the fuselages (1). The power system includes a hydrogen cylinder (7), a hydrogen fuel cell (8), and a battery. The hydrogen cylinder (7) is connected to the hydrogen fuel cell (8) to provide hydrogen to the hydrogen fuel cell (8) to generate electricity. The hydrogen fuel cell (8) is connected to the tail thrust assembly (6). The battery is connected to the rotor assembly (5).

2. The hydrogen-powered twin-fuselage vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, The fuselage (1) is a long and slender streamlined shape with a circular cross section, the wing (2) is a single straight wing with a high aspect ratio, and the tail (3) is an inverted V shape.

3. The hydrogen-powered twin-fuselage vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, Ailerons (9) are provided on both trailing edges of the wing (2). A first servo motor is connected to the aileron (9). The first servo motor controls the aileron (9) to swing, so as to realize the attitude change of the UAV body.

4. The hydrogen-powered twin-fuselage vertical takeoff and landing fixed-wing UAV according to claim 3, characterized in that, Two ailerons (9) are provided on each side of the wing (2), and each of the two ailerons (9) on each side is equipped with a first servo motor. Each first servo motor controls one aileron (9) and is powered independently.

5. The hydrogen-powered twin-fuselage vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, Both sides of the tail fin (3) are provided with operating control surfaces (10), and a second servo motor is connected to the operating control surface (10). The second servo motor controls the swing of the operating control surface (10) to realize the pitch and small-angle turning of the UAV body. There are two operating control surfaces (10) on each side of the tail fin (3). Each of the two operating control surfaces (10) on each side is equipped with a second servo motor. Each servo motor controls one operating control surface (10) and is powered independently.

6. The hydrogen-powered twin-fuselage vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, The rotor assembly (5) is provided in four sets, and the four sets of rotor assemblies (5) are respectively located at the front end and rear end of the two fuselages (1); the rotor assembly (5) includes a rotor propeller (50) and a first drive motor (51). The first drive motor (51) is fixed to the bottom of the fuselage (1) and is connected to the battery. The rotor propeller (50) is mounted on the output shaft of the first drive motor (51). The first drive motor (51) drives the rotor propeller (50) to rotate so as to realize the vertical take-off and landing of the UAV body.

7. The hydrogen-powered twin-fuselage vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, Two sets of tail thrust assemblies (6) are provided, and the two sets of tail thrust assemblies (6) are respectively located at the tail of the two fuselages (1). The tail thrust assembly (6) includes a tail thrust propeller (60) and a second drive motor (61). The second drive motor (61) is fixed at the tail of the fuselage (1) and is connected to the hydrogen fuel cell (8). The tail thrust propeller (60) is mounted on the output shaft of the second drive motor (61). The second drive motor (61) drives the tail thrust propeller (60) to rotate so as to realize the cruise of the UAV body.

8. The hydrogen-powered twin-fuselage vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, Each of the fuselage (1) has an air inlet (11) on its top, which is located above the hydrogen fuel cell (8).

9. The hydrogen-powered twin-fuselage vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, Each of the fuselage (1) is provided with a cooling fan (12) at its bottom, the cooling fan (12) being located below the hydrogen fuel cell (8).

10. The hydrogen-powered twin-fuselage vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, The landing device includes two landing gears (13), which are located at the bottom of the two fuselages (1).

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