Hydrogen energy air-sea cross-medium aircraft

Abstract

The invention provides a hydrogen energy air-sea cross-medium aircraft, which comprises a main body assembly, the main body assembly is provided with a driving assembly, an energy assembly and a control assembly, and the main body assembly comprises a fuselage, wings, wing flaps, a direction tail vane, a top sealing cover, a belly diversion channel, a water ballast tank, a first mounting groove and a second mounting groove; the two wings are symmetrically and fixedly connected to the two sides of the fuselage, the fuselage adopts a bionic marine fish streamline design, wing flaps are installed on one sides of the wings, and a direction tail vane is installed at one end of the fuselage. The advantages of high energy density and long endurance time of hydrogen energy of the hydrogen fuel cell are fully utilized, and the cross-domain operation capability of the cross-medium aircraft is utilized, so that the actual demand problems of ocean development, ocean inspection, safety search and rescue, structural detection in a water area, water quality sampling and the like in a cross-medium range in the air and sea fields are solved; the invention provides the hydrogen energy cross-medium aircraft which has the advantages of long distance, long endurance and cross-domain operation.

Description

Technical Field

[0001] The invention relates to an aircraft, in particular to a hydrogen energy air-sea cross-medium aircraft, belonging to the technical field of aircraft. Background Art

[0002] Unmanned aerial vehicles, also known as drones or unmanned aircraft, are aircraft that fly autonomously without a pilot and rely on remote control or preset programs. They are usually equipped with advanced navigation systems, sensors and communication equipment, and can perform various complex tasks. Unmanned aerial vehicles have a wide range of applications, including military reconnaissance, civil aerial photography, environmental monitoring, disaster assessment, agricultural plant protection, logistics distribution, etc.

[0003] The design and control technology of single-medium UAV systems used underwater or in the air has been relatively mature, and has gradually penetrated into various fields with its own advantages. With the increasing demand for UAVs in downstream markets such as marine development, ecological monitoring, in-water structure detection, and water quality sampling, the application market has also put forward higher requirements for UAVs. Facing the scenarios of simultaneous application in air, water surface and underwater cross-domain three-dimensional space, the existing single-medium UAVs can no longer meet the market demand. However, since the new sea and air amphibious UAVs can efficiently complete cross-domain operations, they have continued to receive attention in recent years. Therefore, the development of cross-medium aircraft is of great significance. In existing research, the endurance problem of cross-medium aircraft has greatly hindered its practical application. Hydrogen fuel cells have a high energy density and can greatly improve the endurance of cross-medium aircraft. Therefore, the development of hydrogen energy cross-medium aircraft also has important application value for assisting the development of the marine industry. For this reason, a hydrogen energy air-sea cross-medium aircraft is proposed. Summary of the invention

[0004] In view of this, the present invention provides a hydrogen-powered air-sea cross-medium aircraft to solve or alleviate one of the technical problems existing in the prior art and at least provide a beneficial option.

[0005] The technical solution of the embodiment of the present invention is implemented as follows: A hydrogen energy air-sea cross-medium aircraft comprises a main body assembly, on which a drive assembly, an energy assembly and a control assembly are installed, and the main body assembly comprises a fuselage, wings, flaps, a directional tail rudder, a top sealing cover, a belly guide channel, a ballast water tank, a first installation slot and a second installation slot; Two wings are symmetrically fixedly connected to both sides of the fuselage. The fuselage adopts a streamlined design imitating marine fish. A wing flap is installed on one side of the wing, a directional tail rudder is installed at one end of the fuselage, a top sealing cover is detachably fixedly connected to the top of the fuselage, a belly diversion channel is arranged at the bottom of the fuselage, a ballast water tank is symmetrically fixedly connected to the inside of the fuselage, a first installation groove is opened at the top of the fuselage, and a second installation groove is opened at the bottom of the fuselage.

[0006] Further preferably: the driving assembly includes a front motor and a folding propeller; A front motor is installed inside the fuselage, and an output shaft of the front motor is fixedly connected to the folding propeller.

[0007] Further preferably: the driving assembly further includes an underwater thruster, a tilting servo, and a bearing; A tilting servo is installed inside the fuselage, two bearings are symmetrically fixedly connected inside the fuselage, the inner sidewalls of the bearings are rotatably connected to an underwater thruster, and the outer sidewalls of the underwater thruster are fixedly connected to the output shaft of the tilting servo.

[0008] Further preferably, the underwater propeller is arranged inside the abdominal diversion channel.

[0009] Further preferably: the energy assembly includes a hydrogen cylinder, an oxygen cylinder, a cylinder mounting seat and a hydrogen fuel cell; A gas cylinder mounting seat is arranged inside the fuselage, a hydrogen cylinder and an oxygen cylinder are symmetrically fixedly connected to the inner side wall of the gas cylinder mounting seat, and a hydrogen fuel cell is installed on the inner side wall of the gas cylinder mounting seat.

[0010] Further preferably, the gas cylinder mounting seat is fixedly connected to the inner side wall of the first mounting groove.

[0011] Further preferably, a battery is installed on one side of the gas cylinder mounting seat.

[0012] Further preferably, the control component includes an integrated electronic system, and the integrated electronic system includes a power module, a controller, a data processing and storage module, a communication module, a navigation module and a switching module.

[0013] Further preferably: the control component also includes a pan / tilt camera and a searchlight; A pan-tilt camera is installed on the inner side wall of the second installation groove, and searchlights are symmetrically installed on both sides of the pan-tilt camera.

[0014] Further preferably, a sensor is installed on the front surface of the fuselage, and the sensor is connected to the integrated electronic system signal.

[0015] The embodiment of the present invention has the following advantages due to the adoption of the above technical solution: 1. The present invention fully utilizes the advantages of high energy density and long endurance of hydrogen energy in hydrogen fuel cells, and utilizes the cross-domain operation capability of cross-media aircraft to solve practical needs such as cross-media marine development, marine inspection, safety search and rescue, in-water structure detection, water quality sampling, etc. in the air and sea fields, and provides a hydrogen energy cross-media aircraft with long-distance, long-flight, and cross-domain operations.

[0016] 2. The present invention adopts a streamlined fuselage design and integrates the fuselage with the wings and rudders, so it has the underwater drag reduction characteristics of marine fish. The hydrogen energy system it carries can generate electricity to provide the required energy for the cross-medium aircraft. The excess electricity is stored in batteries to improve the endurance of the aircraft.

[0017] 3. The present invention provides power for aerial flight through a front motor and folding propellers, uses underwater thrusters to provide power for underwater navigation, and uses wing flaps and directional tail rudders to adjust the posture and movement direction in the air and underwater. It can well meet the air and underwater maneuverability requirements of the aircraft and improve its functionality in cross-domain operations in the air and sea.

[0018] The above summary is for illustrative purposes only and is not intended to be limiting in any way. In addition to the illustrative aspects, embodiments and features described above, further aspects, embodiments and features of the present invention will be readily apparent by reference to the accompanying drawings and the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or technical descriptions will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 It is a structural diagram of the present invention; Figure 2 It is a front structural diagram of the present invention; Figure 3 It is the exploded structure diagram of the present invention; Figure 4 It is a structural diagram of the underwater propeller of the present invention; Figure 5 This is a structural diagram of the present invention after the top sealing cover is removed; Figure 6 It is a bottom view structural diagram of the present invention.

[0021] Figure numerals: 1. main component; 10. fuselage; 11. wing; 12. flap; 13. rudder; 14. top sealing cover; 15. belly diversion channel; 16. ballast water tank; 17. first mounting slot; 18. second mounting slot; 2. drive component; 20. front motor; 21. folding propeller; 22. underwater thruster; 23. tilting servo; 24. bearing; 3. energy component; 30. hydrogen cylinder; 31. oxygen cylinder; 32. cylinder mounting bracket; 33. hydrogen fuel cell; 34. battery; 4. control component; 40. integrated electronic system; 41. gimbal camera; 42. searchlight; 43. sensor. DETAILED DESCRIPTION

[0022] In the following, only some exemplary embodiments are briefly described. As those skilled in the art will appreciate, the described embodiments may be modified in various ways without departing from the spirit or scope of the present invention. Therefore, the drawings and descriptions are considered to be exemplary and non-restrictive in nature.

[0023] The embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0024] Embodiment 1 like Figure 1-Figure 6 As shown, an embodiment of the present invention provides a hydrogen energy air-sea cross-medium aircraft, comprising a main body assembly 1, on which a drive assembly 2, an energy assembly 3 and a control assembly 4 are installed, and the main body assembly 1 comprises a fuselage 10, a wing 11, a flap 12, a directional tail rudder 13, a top sealing cover 14, a belly guide channel 15, a ballast water tank 16, a first installation groove 17 and a second installation groove 18; Two wings 11 are symmetrically fixedly connected to both sides of the fuselage 10. The fuselage 10 adopts a streamlined design imitating marine fish. A wing flap 12 is installed on one side of the wing 11, and a directional tail rudder 13 is installed at one end of the fuselage 10. A top sealing cover 14 is detachably fixedly connected to the top of the fuselage 10, and a belly diversion channel 15 is arranged at the bottom of the fuselage 10. A ballast water tank 16 is symmetrically fixedly connected to the inside of the fuselage 10. A first mounting groove 17 is opened on the top of the fuselage 10, and a second mounting groove 18 is opened at the bottom of the fuselage 10. When the hydrogen-powered air-sea cross-medium aircraft performs cross-domain operation tasks, its ballast water tank 16 is mainly used to inhale or discharge water during the cross-medium movement, so as to enable the body to quickly dive into the water or take off from the water when entering the water. When it is necessary to get out of the water quickly, the ballast tank 16 quickly discharges the water in the tank to reduce its own weight, and sails quickly under the action of buoyancy and the thrust of the underwater propeller 22. The combined action of the flaps 12 and the rudder 13 can keep the head of the fuselage 10 facing upward.

[0025] In this embodiment, specifically: the driving assembly 2 includes a front motor 20 and a folding paddle 21; A front motor 20 is installed inside the fuselage 10, and the output shaft of the front motor 20 is fixedly connected to the folding propeller 21. When the hydrogen-powered air-sea cross-medium aircraft flies in the air, it is driven by the front motor 20 and the folding propeller 21, and the underwater propeller 22 rotates to a horizontal direction with the fuselage 10 to reduce resistance.

[0026] In this embodiment, specifically: the driving assembly 2 further includes an underwater thruster 22, a tilting servo 23, and a bearing 24; A tilting servo 23 is installed inside the fuselage 10, and two bearings 24 are symmetrically fixedly connected inside the fuselage 10. The inner wall of the bearing 24 is rotatably connected to the underwater propeller 22, and the outer wall of the underwater propeller 22 is fixedly connected to the output shaft of the tilting servo 23. When swimming underwater, the front motor 20 and the folding propeller 21 can be turned off, and the underwater propeller 22 located on the belly of the fuselage 10 can provide underwater power. When rapid maneuvering is required, the front motor 20 and the folding propeller 21 can also be turned on to provide part of the underwater forward power. At the same time, the aircraft can realize the control of the posture and movement direction in the air and underwater with the help of the wings 11, the flaps 12 and the directional tail rudder 13.

[0027] In this embodiment, specifically: the underwater propeller 22 is arranged inside the belly diversion channel 15, and is immediately turned on when the front motor 20 and the folding paddle 21 located at the head surface surface, thereby providing flight power for the hydrogen energy cross-medium aircraft. After completely emerging from the water, the underwater propeller 22 is adjusted to a position horizontal to the fuselage 10 under the action of the tilting servo 23 to reduce the resistance generated by the underwater propeller 22. When it is necessary to enter the water quickly, the front motor 20 and the folding paddle 21 at the head are turned off, and after the hydrogen energy cross-medium aircraft lands on the water surface, water is immediately pumped into the ballast tank 16 to make the aircraft submerged. At the same time, the underwater propeller 22 is adjusted to a position vertical to the fuselage 10 by the tilting servo 23, and then it can be turned on to generate underwater thrust. Further adjustment of the flap 12 and the directional tail rudder 13 can control its posture and movement direction underwater.

[0028] Embodiment 2 like Figure 1-Figure 6 As shown, an embodiment of the present invention provides a hydrogen energy air-sea cross-medium aircraft, comprising a main body component 1, on which a driving component 2, an energy component 3 and a control component 4 are installed; In this embodiment, specifically: the energy assembly 3 includes a hydrogen cylinder 30, an oxygen cylinder 31, a cylinder mounting seat 32 and a hydrogen fuel cell 33; A gas cylinder mounting seat 32 is provided inside the fuselage 10, and a hydrogen cylinder 30 and an oxygen cylinder 31 are symmetrically fixedly connected to the inner side wall of the gas cylinder mounting seat 32. A hydrogen fuel cell 33 is installed on the inner side wall of the gas cylinder mounting seat 32. The hydrogen cylinder 30 and the oxygen cylinder 31 provide raw materials for the hydrogen fuel cell 33. The hydrogen fuel cell 33 uses the fuel cell technology in the prior art, which will not be elaborated here.

[0029] In this embodiment, specifically: the gas cylinder mounting seat 32 is fixedly connected to the inner wall of the first mounting groove 17 .

[0030] In this embodiment, specifically: a battery 34 is installed on one side of the gas cylinder mounting seat 32 , and excess electric energy is stored inside the battery 34 .

[0031] The hydrogen energy air-sea cross-medium aircraft energy system is composed of a hydrogen cylinder 30, an oxygen cylinder 31, a cylinder mounting seat 32 and a hydrogen fuel cell 33. Compared with the traditional battery energy system, it has the advantages of long flight time and long distance. It can maintain a long-term working state, while traditional aircraft are often difficult to successfully perform one-step maintenance in the long-distance marine engineering equipment maintenance due to the long distance and energy consumption problems. This feature of the hydrogen energy air-sea cross-medium aircraft provides a more reliable solution for the maintenance of long-distance marine engineering equipment.

[0032] Embodiment 3 like Figure 1-Figure 6 As shown, an embodiment of the present invention provides a hydrogen energy air-sea cross-medium aircraft, comprising a main body component 1, on which a driving component 2, an energy component 3 and a control component 4 are installed; In this embodiment, specifically: the control component 4 includes an integrated electronic system 40, the integrated electronic system 40 includes a power module, a controller, a data processing and storage module, a communication module, a navigation module and a switching module, when the hydrogen energy air-sea cross-medium aircraft is performing a mission, the ground station can send instructions to the integrated electronic system 40 to plan the flight path of the aircraft and remotely control the aircraft through the ground station.

[0033] In this embodiment, specifically: the control component 4 also includes a pan / tilt camera 41 and a searchlight 42; A pan-tilt camera 41 is installed on the inner wall of the second installation groove 18, and searchlights 42 are symmetrically installed on both sides of the pan-tilt camera 41. During the execution of the mission, the pan-tilt camera 41 and the searchlight 42 can be controlled and adjusted to shoot the target in the air or underwater.

[0034] In this embodiment, specifically: a sensor 43 is installed on the front surface of the fuselage 10, the sensor 43 is signal-connected to the integrated electronic system 40, and data is collected through the sensor 43. The sensor 43 is a combination of two or more of a temperature and humidity sensor, a pressure sensor, a lidar sensor, an infrared image sensor, an electrochemical gas sensor, and a fluxgate magnetometer.

[0035] When the present invention is working: the fuselage 10 of the hydrogen energy cross-medium aircraft adopts a streamlined design and is close to the shape of marine fish. At the same time, the fuselage 10, the wings 11 and the directional tail rudder 13 are integrated to greatly reduce its navigation resistance in the air and underwater; the fuselage 10 has a belly diversion channel 15, in which an underwater propeller 22 is installed, and a folding propeller 21 for flight is installed at the front head of the fuselage 10. The electric energy generated by the hydrogen energy battery 33 used in the hydrogen energy air-sea cross-medium aircraft can be stored by the battery 34, and the product water can be discharged to the ballast water tank 16 located in the wings 11 on both sides for storage or release. When the cross-medium aircraft flies in the air, it is driven by the front motor 20 and the folding propeller 21. At this time, the underwater propeller 22 rotates to the horizontal direction with the fuselage 10 to reduce resistance; when swimming underwater, the front motor 20 and the folding propeller 21 can be turned off or turned on to provide additional power, but the underwater power is mainly provided by the underwater propeller 22 located in the belly of the fuselage 10. The hydrogen-powered air-sea cross-medium aircraft uses flaps 12 and directional rudders 13 to control the attitude and direction of movement in the air and underwater. The ballast tank 16 is mainly used to inhale or discharge water during cross-medium movement, so as to enable the body to quickly dive into the water or take off from underwater when entering the water. The installation groove is watertight and is located inside the fuselage 10 of the hydrogen-powered cross-medium aircraft. It is used to place electronic components such as flight control, electric regulation, batteries, etc. that need to be sealed. Since hydrogen fuel cells have a high energy density, the cross-medium aircraft can be operated for a long time. Therefore, the hydrogen-powered cross-medium aircraft has the ability to perform long-distance, long-time, and fast maneuvering operations.

[0036] The basic principles of the present disclosure are described above in conjunction with specific embodiments. However, it should be noted that the advantages, strengths, effects, etc. mentioned in the present disclosure are only examples and not limitations, and it cannot be considered that these advantages, strengths, effects, etc. are required by each embodiment of the present disclosure. In addition, the specific details disclosed above are only for the purpose of illustration and ease of understanding, and are not limiting. The above details do not limit the present disclosure to the necessity of adopting the above specific details to be implemented.

[0037] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of various changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A hydrogen-powered air-sea cross-medium aircraft, comprising a main body assembly (1), characterized in that: The main body component (1) is mounted with a drive component (2), an energy component (3) and a control component (4); the main body component (1) comprises a fuselage (10), a wing (11), a wing flap (12), a rudder (13), a top sealing cover (14), a belly guide channel (15), a ballast tank (16), a first mounting groove (17) and a second mounting groove (18); Two wings (11) are symmetrically fixedly connected to both sides of the fuselage (10); the fuselage (10) adopts a streamlined design imitating marine fish; a wing flap (12) is installed on one side of the wing (11); a directional tail rudder (13) is installed at one end of the fuselage (10); a top sealing cover (14) is detachably fixedly connected to the top of the fuselage (10); a belly diversion channel (15) is provided at the bottom of the fuselage (10); a ballast water tank (16) is symmetrically fixedly connected to the inside of the fuselage (10); a first installation groove (17) is provided at the top of the fuselage (10); and a second installation groove (18) is provided at the bottom of the fuselage (10).

2. A hydrogen-powered air-sea cross-medium aircraft according to claim 1, characterized in that: The driving assembly (2) comprises a front motor (20) and a folding paddle (21); A front motor (20) is installed inside the fuselage (10), and an output shaft of the front motor (20) is fixedly connected to the folding propeller (21).

3. A hydrogen-powered air-sea cross-medium aircraft according to claim 2, characterized in that: The driving assembly (2) further comprises an underwater propeller (22), a tilting servo (23), and a bearing (24); A tilting servo (23) is installed inside the fuselage (10), two bearings (24) are symmetrically fixedly connected inside the fuselage (10), an underwater propeller (22) is rotatably connected to the inner wall of the bearing (24), and an outer wall of the underwater propeller (22) is fixedly connected to the output shaft of the tilting servo (23).

4. A hydrogen-powered air-sea cross-medium aircraft according to claim 3, characterized in that: The underwater propeller (22) is arranged inside the abdominal diversion channel (15).

5. The hydrogen-powered air-sea cross-medium aircraft according to claim 1, characterized in that: The energy component (3) comprises a hydrogen cylinder (30), an oxygen cylinder (31), a cylinder mounting seat (32) and a hydrogen fuel cell (33); A gas cylinder mounting seat (32) is provided inside the fuselage (10), a hydrogen cylinder (30) and an oxygen cylinder (31) are symmetrically fixedly connected to the inner side wall of the gas cylinder mounting seat (32), and a hydrogen fuel cell (33) is installed on the inner side wall of the gas cylinder mounting seat (32).

6. A hydrogen-powered air-sea cross-medium aircraft according to claim 5, characterized in that: The gas cylinder mounting seat (32) is fixedly connected to the inner side wall of the first mounting groove (17).

7. A hydrogen-powered air-sea cross-medium aircraft according to claim 5, characterized in that: A storage battery (34) is mounted on one side of the gas cylinder mounting seat (32).

8. The hydrogen-powered air-sea cross-medium aircraft according to claim 1, characterized in that: The control component (4) comprises an integrated electronic system (40), and the integrated electronic system (40) comprises a power module, a controller, a data processing and storage module, a communication module, a navigation module, and a switching module.

9. A hydrogen-powered air-sea cross-medium aircraft according to claim 8, characterized in that: The control component (4) further includes a pan / tilt camera (41) and a searchlight (42); A pan-tilt camera (41) is installed on the inner side wall of the second installation groove (18), and searchlights (42) are symmetrically installed on both sides of the pan-tilt camera (41).

10. The hydrogen-powered air-sea cross-medium aircraft according to claim 8, characterized in that: A sensor (43) is installed on the front surface of the fuselage (10), and the sensor (43) is connected to the integrated electronic system (40) by signal.

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