Cross-medium aircraft and cross-medium flight method thereof

Abstract

The invention discloses a cross-medium aircraft and a cross-medium flight method thereof, and relates to the technical field of aircrafts, the cross-medium aircraft comprises an aircraft body and an oxyhydrogen blast chamber, the oxyhydrogen blast chamber is arranged on the aircraft body, the oxyhydrogen blast chamber comprises a shell, a water electrolysis device, an electronic ignition device and a water pump, the water electrolysis device is arranged in an inner cavity of the shell, and the water electrolysis device is arranged in the inner cavity of the shell; the electronic ignition device is arranged on the inner wall face of the shell, a water inlet of the water pump is communicated with an inner cavity of the shell, and a pressure outlet is formed in the bottom of the shell. An inner cavity of the shell is filled with water through the water pump, hydrogen and oxygen are generated through the water electrolysis device, at the moment, the aircraft can naturally float to the water surface, then gas in the inner cavity is ignited through the electronic ignition device, burning and explosion can be generated, pushing force is generated, the aircraft is pushed out of water, and the oxyhydrogen burning and explosion chamber adopts a gas burning and explosion mode as power; the aircraft can adapt to the underwater environment, the adaptability of the aircraft is improved, meanwhile, energy loss is reduced, and the mass of the whole aircraft is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to a trans-medium aircraft and a trans-medium flight method thereof. Background Art

[0002] A trans-medium aircraft is an aircraft that can navigate in two media, air and water, integrating the characteristics of underwater vehicles and unmanned aerial vehicles, and is suitable for multi-scenario tasks such as marine search, rescue, and communication relay. Such aircraft can not only achieve rapid deployment and maneuverable flight in the air, but also have the concealment of underwater navigation, and can meet the multi-task requirements in complex environments, and have broad application prospects in natural disaster rescues such as floods, typhoons, tsunamis, and shipwrecks, and military reconnaissance fields.

[0003] At present, the power systems of trans-medium aircraft known to the applicant mainly adopt energy forms such as lithium batteries, fuel cells, and aviation fuels, but face many technical challenges during trans-medium navigation: First, the energy adaptability problem: the underwater environment lacks oxygen, and traditional fuels (such as aviation kerosene) are difficult to burn underwater, resulting in the propulsion system being difficult to work efficiently; Second, the energy loss problem: the physical properties of air and liquid media vary greatly (such as sudden changes in resistance and density), resulting in excessive energy loss during the medium conversion process of the aircraft, reducing the overall navigation efficiency; Third, the system mass problem: current aircraft usually rely on battery power supply, the battery has a large mass and limited endurance, increasing the load of the aircraft and restricting the performance of the trans-medium aircraft.

[0004] Therefore, there is an urgent need for a trans-medium aircraft with strong adaptability, low energy loss, and small mass. Summary of the Invention

[0005] The purpose of the present invention is to provide a trans-medium aircraft and a trans-medium flight method thereof to solve the problems existing in the above-mentioned prior art, achieve the trans-medium of the aircraft through a hydrogen-oxygen combustion chamber, improve adaptability, reduce energy loss, and reduce the overall mass of the aircraft.

[0006] To achieve the above purpose, the present invention provides the following solution: The present invention provides a trans-medium aircraft, including an aircraft body and a hydrogen-oxygen combustion chamber. The hydrogen-oxygen combustion chamber is arranged on the aircraft body. The hydrogen-oxygen combustion chamber includes a housing, an electrolytic water device, an electronic ignition device, and a water pump. The electrolytic water device is arranged in the inner cavity of the housing. The electronic ignition device is arranged on the inner wall surface of the housing. The water inlet of the water pump is communicated with the inner cavity of the housing. A pressure outlet is arranged at the bottom of the housing.

[0007] Preferably, the electronic ignition device is arranged at the upper part of the inner side wall of the housing.

[0008] Preferably, the bottom of the outer shell is provided with a constricted opening to form the pressure outlet.

[0009] Preferably, a plurality of the hydrogen-oxygen combustion chambers are evenly arranged on the aircraft body.

[0010] Preferably, the aircraft body includes a support plate, a controller, a power supply battery, a plurality of connecting arms, motors, and rotors. The controller and the power supply battery are both arranged on the support plate. A plurality of the connecting arms are evenly arranged around the support plate. An installation seat is arranged at one end of the connecting arm away from the support plate. The motor is arranged in the installation seat. The motor is in transmission connection with the rotor. The hydrogen-oxygen combustion chamber is arranged on the support plate. The electrolytic water device, the electronic ignition device, and the water pump of the hydrogen-oxygen combustion chamber are all electrically connected to the controller.

[0011] Preferably, a reserve power source is arranged at the bottom of the support plate.

[0012] Preferably, the power supply battery is located above the controller, and the water pump is located between the support plate and the power supply battery.

[0013] Preferably, the support plate and the connecting arms are both made of carbon fiber composite materials, and the rotor is made of fiber reinforced materials.

[0014] Preferably, the inner cavity of the outer shell is communicated with the water pump through an electromagnetic valve.

[0015] The present invention also provides a cross-medium flight method for the above cross-medium aircraft, including the following steps:

[0016] S1: When the aircraft is in water, start the water pump to pump water into the inner cavity of the outer shell of the hydrogen-oxygen combustion chamber;

[0017] S2: Start the electrolytic water device to electrolyze the water in the inner cavity of the outer shell to form hydrogen and oxygen, and the aircraft gradually floats out of the water surface to achieve preliminary water emergence;

[0018] S3: Start the electronic ignition device to ignite the gas in the inner cavity to cause a violent explosion, and the remaining water in the inner cavity is ejected from the pressure outlet to generate a thrust to push the aircraft out of the water surface;

[0019] S4: After the aircraft emerges from the water, provide lift through the rotors of the aircraft body to make the aircraft smoothly enter the flight mode.

[0020] The present invention mainly achieves the following technical effects compared with the prior art:

[0021] When transitioning from underwater to air, first use a water pump to fill the inner cavity of the outer shell with water, and then use an electrolytic water device to generate hydrogen and oxygen. At this time, the aircraft can generate a certain buoyancy and naturally float to the water surface. Finally, use an electronic ignition device to ignite the gas in the inner cavity to produce an explosion and generate a driving force to push the aircraft out of the water. The hydrogen-oxygen explosion chamber uses the method of explosive gas as power, which can adapt to the underwater environment, improve the adaptability of the aircraft, and at the same time use the buoyancy generated by the gas to enable the aircraft to move to the water surface, reducing energy loss, and also conducive to reducing the volume of the battery and lowering the overall mass of the aircraft.

[0022] The following technical effects are achieved by other solutions of the present invention compared with the prior art:

[0023] The pressure outlet with a constricted opening can effectively increase the driving force generated by the hydrogen-oxygen explosion chamber, ensuring that the aircraft can quickly and effectively leave the water surface.

[0024] Multiple uniformly arranged hydrogen-oxygen explosion chambers can provide a stable upward driving force for the aircraft, ensuring a stable attitude of the aircraft after leaving the water surface. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0026] Figure 1 It is a schematic structural diagram of the cross-media aircraft in the embodiment of the present invention;

[0027] Figure 2 It is a schematic central cross-sectional view of the cross-media aircraft in the embodiment of the present invention;

[0028] Figure 3 It is a schematic distribution diagram of the hydrogen-oxygen explosion propellers in the embodiment of the present invention;

[0029] Figure 4 It is a schematic internal structure diagram of the hydrogen-oxygen explosion chamber in the embodiment of the present invention;

[0030] Among them, 1. Motor; 2. Rotor; 3. Mounting seat; 4. Hydrogen-oxygen explosion chamber; 5. Reserve power supply; 6. Connecting arm; 7. Power supply battery; 8. Outer shell; 9. Inner cavity; 10. Pressure outlet; 11. Support plate; 12. Controller; 13. Water pump; 14. Electronic ignition device; 15. Electrode rod. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0031] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0032] The object of the present invention is to provide a cross-media aircraft and its cross-media flight method to solve the problems existing in the prior art. By means of a hydrogen-oxygen combustion chamber, the cross-media of the aircraft is realized, while improving the adaptability, reducing the energy loss and reducing the overall mass of the aircraft.

[0033] To make the above objects, features and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0034] Please refer to as Figures 1 to 4 shown, a cross-media aircraft is provided, including an aircraft body and a hydrogen-oxygen combustion chamber 4. The hydrogen-oxygen combustion chamber 4 is arranged on the aircraft body. The hydrogen-oxygen combustion chamber 4 includes a housing 8, a water electrolysis device, an electronic ignition device 14 and a water pump 13. The water electrolysis device is arranged in the inner cavity 9 of the housing 8. Specifically, the two electrode rods 15 of the water electrolysis device can be arranged in the inner cavity 9. The electronic ignition device 14 is arranged on the inner wall surface of the housing 8, which can be the inner top wall or the inner side wall. The water inlet of the water pump 13 is communicated with the inner cavity 9 of the housing 8. A pressure outlet 10 is arranged at the bottom of the housing 8. The cross-media principle of this aircraft is as follows: when crossing from underwater to air, first use the water pump 13 to fill the inner cavity 9 of the housing 8 with water, and then use the water electrolysis device to generate hydrogen and oxygen. At this time, the aircraft can generate a certain buoyancy and float naturally to the water surface. Finally, use the electronic ignition device 14 to ignite the gas in the inner cavity 9 to generate an explosion to produce a driving force to push the aircraft out of the water. The hydrogen-oxygen combustion chamber 4 uses the combustion gas as the power, which can adapt to the underwater environment, improve the adaptability of the aircraft, and at the same time use the buoyancy generated by the gas to realize the movement of the aircraft to the water surface, reduce the energy loss, and is beneficial to reducing the volume of the battery and reducing the overall mass of the aircraft; when crossing from air to water, directly control the aircraft to land on the water surface, and use the water pump 13 to fill the inner cavity 9 of the housing 8 with water to discharge the air in the inner cavity 9 to realize the sinking of the aircraft into the water.

[0035] The horizontal height of the pressure outlet 10 should be lower than the lower surface of the aircraft body to ensure that when the pressure outlet 10 is separated from the water surface during the aircraft's water exit process, the aircraft body has already left the water surface. During the aircraft's water entry process, the pressure outlet 10 can contact the water surface first to cooperate with the water pump 13 to complete the water filling as soon as possible.

[0036] The water inlet of the water pump 13 is connected to the top of the inner cavity 9, so that the gas in the inner cavity 9 can be exhausted as much as possible when filling with water.

[0037] The inner cavity 9 of the shell 8 is connected to the water pump 13 through an electric control valve. The electric control valve can be closed when explosion is in progress and controlled to open when water filling is required. The electric control valve can be an electric control ball valve.

[0038] In this embodiment, the electronic ignition device 14 is arranged on the upper part of the inner wall of the outer shell 8, which can provide greater combustion and explosion power, thereby making the upward thrust of the aircraft greater, and fully utilizing the hydrogen-oxygen combustion and explosion energy.

[0039] The bottom of the shell 8 is narrowed to form a pressure outlet 10, which can effectively increase the driving force generated by the hydrogen-oxygen explosion chamber 4 and ensure that the aircraft can quickly and effectively leave the water surface.

[0040] In this embodiment, the housing 8 includes a cylinder and a frustoconical cylinder. The large-diameter end of the frustoconical cylinder is connected to the cylinder and has the same inner diameter as the cylinder, and the small-diameter end serves as a pressure outlet 10 .

[0041] Several hydrogen-oxygen explosion chambers 4 are evenly arranged on the aircraft body, which can provide a stable upward propulsion for the aircraft and ensure the stability of the aircraft after leaving the water surface; in this embodiment, four hydrogen-oxygen explosion chambers 4 are evenly arranged on the aircraft body.

[0042] A pressure sensor may be provided at the pressure outlet 10 to monitor the pressure of the injection fluid and provide feedback, thereby achieving safety protection and precise control.

[0043] The aircraft body includes a support plate 11, a controller 12, a power supply battery 7, a plurality of connecting arms 6, a motor 1 and a rotor 2. The controller 12 and the power supply battery 7 are both arranged on the support plate 11. A plurality of connecting arms 6 are evenly arranged around the support plate 11. A mounting seat 3 is arranged at one end of the connecting arm 6 away from the support plate 11. The motor 1 is arranged in the mounting seat 3. The motor 1 is transmission-connected to the rotor 2. A high-performance brushless DC motor can be selected for the motor 1. The hydrogen-oxygen combustion chamber 4 is arranged on the support plate 11. The water electrolysis device, the electronic ignition device 14 and the water pump 13 of the hydrogen-oxygen combustion chamber 4 are all electrically connected to the controller 12. The controller 12 also adjusts the output speed of the motor 1 through an electronic speed regulator to control the rotation speed of the rotor 2.

[0044] In this embodiment, four connecting arms 6 are provided, and the support plate 11 is in a square structure. The four connecting arms 6 are respectively connected to the four corners of the support plate 11 , and the four hydrogen-oxygen combustion chambers 4 are also provided at the bottom of the four corners of the support plate 11 .

[0045] In order to improve the endurance of the aircraft, the aircraft body also includes a reserve power source 5, which cooperates with the power supply battery 7 to provide more power storage and supply.

[0046] The reserve power source 5 is arranged at the bottom of the support plate 11 to lower the center of gravity and improve the flight stability.

[0047] In this embodiment, the power supply battery 7 is located above the controller 12. The controller 12 is installed on the upper surface of the support plate 11, and the water pump 13 is located between the support plate 11 and the power supply battery 7, which improves the overall structural compactness and reduces the space occupation.

[0048] In order to further reduce the mass of the overall aircraft and ensure the structural strength, the materials of the support plate 11 and the connecting arm 6 are both carbon fiber composite materials, and the material of the rotor 2 is fiber reinforced material.

[0049] On the basis of ensuring the structural strength, grooves can be formed on the connecting arm 6 to further reduce the mass of the aircraft.

[0050] The present invention also provides a cross-medium flight method for the above cross-medium aircraft, including the following steps:

[0051] S1: The aircraft is located in water. The controller 12 controls to start the water pump 13 to create a negative pressure environment in the inner cavity 9 of the outer shell 8, and uses the negative pressure to pump water into the inner cavity 9 of the outer shell 8 of the hydrogen-oxygen combustion chamber 4.

[0052] S2: Start the electrolytic water device. The two electrode rods 15 of the electrolytic water device electrolyze the water in the inner cavity 9 of the outer shell 8 to form hydrogen and oxygen. As hydrogen and oxygen are generated, the aircraft obtains buoyancy, and under the action of the buoyancy, the aircraft gradually emerges from the water surface to achieve initial water emergence.

[0053] S3: Start the electronic ignition device 14 to ignite the gas in the inner cavity 9 to cause a violent explosion. The high temperature and high pressure generated by the explosion force the residual water in the inner cavity 9 to spray out from the pressure outlet 10, generating a thrust to push the aircraft out of the water surface.

[0054] S4: After the aircraft emerges from the water, the rotor 2 of the aircraft body provides lift to enable the aircraft to smoothly enter the flight mode.

[0055] Steps S1 - S4 are the cross-medium process of the aircraft from water to air. In the cross-medium process from air to water, directly control the aircraft to land on the water surface, and fill the inner cavity 9 with water through the water pump 13.

[0056] Adaptations made according to actual requirements are all within the protection scope of the present invention.

[0057] It should be noted that for those skilled in the art, it is obvious that the present invention is not limited to the details of the above-described exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be embraced within the present invention. Any reference signs in the claims should not be construed as limiting the claims involved.

[0058] Specific examples are used in the present invention to illustrate the principles and implementation manners of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention. At the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A cross-medium aircraft, characterized in that It includes an aircraft body and a hydrogen-oxygen combustion chamber, the hydrogen-oxygen combustion chamber is arranged on the aircraft body, the hydrogen-oxygen combustion chamber includes a housing, a water electrolysis device, an electronic ignition device and a water pump, the water electrolysis device is arranged in the inner cavity of the housing, the electronic ignition device is arranged on the inner wall surface of the housing, the water inlet of the water pump is communicated with the inner cavity of the housing, and a pressure outlet is arranged at the bottom of the housing.

2. The cross-medium aircraft according to claim 1, wherein The electronic ignition device is arranged at the upper part of the inner side wall of the housing.

3. The cross-media aircraft according to claim 1, wherein, The bottom of the housing is provided with a reduced opening to form the pressure outlet.

4. The cross-medium aircraft according to claim 1, wherein A plurality of the hydrogen-oxygen combustion chambers are uniformly arranged on the aircraft body.

5. The cross-medium aircraft according to claim 1, characterized in that, The aircraft body includes a support plate, a controller, a power supply battery, a plurality of connecting arms, a motor and a rotor, the controller and the power supply battery are both arranged on the support plate, a plurality of the connecting arms are uniformly arranged around the support plate, a mounting seat is arranged at one end of the connecting arm away from the support plate, the motor is arranged in the mounting seat, the motor is in transmission connection with the rotor, the hydrogen-oxygen combustion chamber is arranged on the support plate, and the water electrolysis device, the electronic ignition device and the water pump of the hydrogen-oxygen combustion chamber are all electrically connected to the controller.

6. The cross-medium aircraft according to claim 5, wherein, A reserve power supply is arranged at the bottom of the support plate.

7. The cross-medium aircraft according to claim 5, characterized in that, The power supply battery is located above the controller, and the water pump is located between the support plate and the power supply battery.

8. The cross-medium aircraft according to claim 5, characterized in that The support plate and the connecting arms are both made of carbon fiber composite materials, and the rotor is made of fiber reinforced materials.

9. The cross-medium aircraft according to claim 1, wherein The inner cavity of the housing is communicated with the water pump through an electric control valve.

10. A cross-medium flight method for a cross-medium aircraft, characterized in that, Applying the cross-medium aircraft according to any one of claims 1-9, includes the following steps: S1: The aircraft is in water, start the water pump, and pump water into the inner cavity of the housing of the hydrogen-oxygen combustion chamber; S2: Start the water electrolysis device, electrolyze the water in the inner cavity of the housing to form hydrogen and oxygen, and the aircraft gradually floats out of the water to achieve initial water emergence; S3: Start the electronic ignition device, ignite the gas in the inner cavity to cause violent combustion and explosion, and the remaining water in the inner cavity is ejected from the pressure outlet to generate thrust to push the aircraft out of the water; S4: After the aircraft emerges from the water, provide lift through the rotor of the aircraft body to make the aircraft smoothly enter the flight mode.

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