Cross-medium aircraft

Abstract

The invention discloses a cross-medium aircraft. The cross-medium aircraft comprises an aircraft main body and a power mechanism for driving the aircraft main body to fly in a cross-medium manner, the power mechanism comprises a reaction cavity formed in the aircraft main body and used for storing water, a jet orifice for jetting water flow is formed in the tail end of the reaction cavity in the advancing direction of the reaction cavity, and the jet orifice faces the direction, away from the advancing direction, of the reaction cavity; a water electrolysis mechanism is arranged at the head end of the reaction cavity in the advancing direction of the reaction cavity, the water electrolysis mechanism is provided with two phases of electrodes extending into the reaction cavity, and the two electrodes are distributed at intervals; an electronic ignition mechanism for igniting hydrogen-oxygen mixed gas is arranged in the reaction cavity, so that two medium environments of air and water can be adapted, seamless switching between underwater propulsion and air flight is realized, and the cross-medium adaptability is improved.

Description

Technical Field

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

[0002] A trans-medium aircraft is a new concept water-air aircraft that can navigate in water and fly in the air. It can achieve rapid deployment and high-speed flight in the air, and also has the concealment of underwater navigation. It is an integrated new device with multi-task capabilities.

[0003] The propulsion method and power source of a trans-medium aircraft directly affect the motion performance of the aircraft and need to be able to adapt to both water and air media. For current trans-medium aircraft, the main power sources include: traditional aviation fuels such as aviation kerosene; proton exchange membrane fuel cells; and lithium batteries. And electric motors are used to construct the power system. However, these power solutions all have certain limitations: First, aviation fuels are limited by the underwater oxygen-deficient environment, and their applications are difficult to meet actual needs; Second, proton exchange membrane fuel cells have the characteristics of clean energy, but their equipment complexity and energy density limit the endurance of the aircraft; Third, although lithium batteries have a high power output, they have problems such as difficult underwater charging and insufficient energy density.

[0004] More importantly, the difficulty in the research of trans-medium aircraft lies in the drastic change in medium resistance during the trans-medium conversion process (such as from air to water, or from water to air), resulting in excessive energy loss during the trans-medium conversion of the trans-medium aircraft. Significantly limiting the motion performance and endurance of the trans-medium aircraft. Summary of the Invention

[0005] The purpose of the present invention is to provide a trans-medium aircraft to solve the problems existing in the prior art, be able to adapt to both air and water media environments, achieve seamless switching between underwater propulsion and air flight, and improve trans-medium adaptability.

[0006] To achieve the above purpose, the present invention provides the following solution: The present invention provides a trans-medium aircraft, including an aircraft main body and a power mechanism for driving the aircraft main body to fly across media;

[0007] The power mechanism includes a reaction chamber opened on the aircraft main body and used for storing water. The tail end of the reaction chamber in its traveling direction is provided with a jet port for water flow to eject, and the jet port faces away from the direction in which the reaction chamber travels; the head end of the reaction chamber in its traveling direction is provided with an electrolytic water mechanism, and the electrolytic water mechanism is provided with electrodes with both phases extending into the interior of the reaction chamber, and the two electrodes are distributed at intervals; an electronic ignition mechanism for igniting hydrogen-oxygen mixed gas is arranged in the reaction chamber.

[0008] Preferably, the electrode has a strip structure, one end of which is fixed at the head end position of the reaction chamber, and the other end extends towards the tail end of the reaction chamber.

[0009] Preferably, the length of the electrode is one-half to three-fourths of the length of the reaction chamber along its traveling direction.

[0010] Preferably, the electronic ignition mechanism is located at a position near the head end of the reaction chamber.

[0011] Preferably, a detection mechanism for detecting the concentration of hydrogen-oxygen gas is further provided at a position near the head end of the reaction chamber, and the detection mechanism is electrically connected to the electronic ignition mechanism.

[0012] Preferably, a nozzle is coaxially connected to the injection port, and the flow cross-section of the nozzle gradually increases along the direction of water flow ejection.

[0013] Preferably, the part of the reaction chamber connected to the injection port has a conical structure, and its flow cross-section gradually decreases along the direction of water flow ejection.

[0014] Preferably, the reaction chamber is equipped with a water filling mechanism for filling water into it. The water filling mechanism includes a negative pressure pump installed outside the reaction chamber. A negative pressure suction pipe is connected between the negative pressure pump and the reaction chamber, and a conduction valve is provided on the negative pressure suction pipe.

[0015] Preferably, ground effect wing airfoils symmetrically distributed on both sides of the reaction chamber are further provided on the aircraft body. Wing end plates are provided at the ends of each ground effect wing airfoil facing away from the reaction chamber, and the wing end plates extend in the vertical direction.

[0016] Preferably, a tail wing is further provided on the aircraft body. The tail wing includes a vertical tail wing connected to the top of the tail end of the reaction chamber, and a horizontal tail wing is connected to the top of the vertical tail wing.

[0017] The present invention has achieved the following technical effects compared with the prior art:

[0018] The disclosed cross-medium aircraft of the present invention, after submerging into water, water flows into and fills the reaction chamber through the injection port. The electrolytic water mechanism generates a hydrogen-oxygen mixed gas through electrolyzing water, and makes the interior of the reaction chamber present a closed state filled with a gas-liquid mixture. When it is necessary to emerge from the water, first, keep the entire aircraft body in a state with the head section facing upward and the tail end facing downward. The hydrogen-oxygen mixed gas in the reaction chamber gathers at the top position of the reaction chamber. The electronic ignition mechanism ignites the hydrogen-oxygen mixed gas in the reaction chamber, and a violent combustion explosion occurs at the top position of the reaction chamber. The temperature and pressure in the reaction chamber rapidly increase, and the shock wave generated by the combustion explosion forces the water in the reaction chamber to flow out of the reaction chamber through the injection port, generating the required thrust to ensure the power demand during the operation mode and providing excellent acceleration performance for the aircraft body. And it can adapt to two medium environments of air and water, realize seamless switching between underwater propulsion and air flight, and improve cross-medium adaptability. After the aircraft body finishes gliding and submerges into water again, water is re-filled into its reaction chamber through the injection port, and the electrolytic water mechanism is used to electrolyze the water in the reaction chamber again to generate hydrogen and oxygen gases, realizing rapid power cycle and repeated launching of the aircraft body. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] 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 to be used 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 also be obtained based on these drawings.

[0020] Figure 1 Schematic diagram of the external shape of the cross-medium aircraft in an embodiment of the present invention;

[0021] Figure 2 Schematic diagram of the external shape of the tail of the cross-medium aircraft in an embodiment of the present invention;

[0022] Figure 3 Schematic diagram of the connection between the reaction chamber and components such as a negative pressure pump in an embodiment of the present invention;

[0023] Figure 4 Schematic diagram of the internal structure of the reaction chamber in an embodiment of the present invention;

[0024] Wherein, 1 - ground effect wing, 2 - reaction chamber housing, 3 - wing end plate, 4 - horizontal tail, 5 - vertical tail, 6 - power supply battery, 7 - reaction chamber, 8 - injection port, 9 - conical structure, 10 - negative pressure pump, 11 - negative pressure suction pipe, 12 - conduction valve, 13 - detection mechanism, 14 - electrolytic water mechanism, 15 - electrolytic rod, 16 - electronic ignition mechanism, 17 - nozzle. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0025] 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.

[0026] The object of the present invention is to provide a cross-media aircraft to solve the problems existing in the prior art, which can adapt to two media environments of air and water, realize seamless switching between underwater propulsion and air flight, and improve cross-media adaptability.

[0027] In order 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.

[0028] As Figures 1 to 4 shown, this embodiment provides a cross-media aircraft, whose application scenario is limited to the scenario of emerging from underwater to the air and gliding in the air for a short time, and does not involve the process of traveling underwater and continuously traveling in the air. The cross-media aircraft disclosed in the present invention includes an aircraft main body and a power mechanism for driving the aircraft main body to fly across media. Preferably, the aircraft main body is integrally formed of transparent acrylic material; the power mechanism includes a reaction chamber 7 opened on the aircraft main body and used for storing water. A jet port 8 for spraying water flow is opened at the tail end of the reaction chamber 7 along its traveling direction, and the jet port 8 faces away from the direction in which the reaction chamber 7 travels; an electrolytic water mechanism 14 is provided at the head end of the reaction chamber 7 along its traveling direction. The electrolytic water mechanism 14 is provided with electrodes both phases of which extend into the interior of the reaction chamber 7, and the two electrodes are spaced apart; an electronic ignition mechanism 16 for igniting the hydrogen-oxygen mixed gas is provided in the reaction chamber 7. Preferably, the electronic ignition mechanism 16 adopts a waterproof electronic igniter to prevent the electronic ignition mechanism 16 from being damaged due to long-term contact with water in the reaction chamber 7.

[0029] The cross-media aircraft disclosed in the present invention, after it submerges into water, water flows into and fills the reaction chamber 7 through the injection port 8. The electrolytic water mechanism 14 generates a hydrogen-oxygen mixed gas through electrolysis of water, and makes the inside of the reaction chamber 7 present a sealed state filled with a gas-liquid mixture; when it is necessary to emerge from the water, first keep the entire aircraft body in a state where the head section is upward and the tail end is downward. The hydrogen-oxygen mixed gas in the reaction chamber 7 gathers at the top position of the reaction chamber 7. The electronic ignition mechanism 16 ignites the hydrogen-oxygen mixed gas in the reaction chamber 7, and a violent combustion explosion occurs at the top position of the reaction chamber 7. The temperature and pressure in the reaction chamber 7 rapidly increase, and the shock wave generated by the combustion explosion forces the water in the reaction chamber 7 to flow out of the reaction chamber 7 through the injection port 8, generating the required thrust to ensure the power demand during the operation mode and providing excellent acceleration performance for the aircraft body. And it can adapt to two media environments of air and water, realizing seamless switching between underwater propulsion and air flight, and improving cross-media adaptability. After the aircraft body glides and submerges into water again, water is re-filled into the reaction chamber 7 through the injection port 8, and the electrolytic water mechanism 14 is used to electrolyze the water in the reaction chamber 7 again to generate hydrogen and oxygen gases, realizing rapid power cycle and repeated launch of the aircraft body. And the present invention uses water as a reactant, electrolyzes to generate hydrogen and oxygen, realizes the recycling of clean energy, and makes the cross-media aircraft disclosed in the present invention have the characteristics of clean energy recycling and efficient propulsion. In addition, water is filled into the reaction chamber 7, and then the electrolytic water mechanism 14 is used to electrolyze the water flow in the reaction chamber 7 to generate a hydrogen-oxygen mixed gas for subsequent combustion explosion. That is to say, the present invention using water as a reactant can effectively utilize natural resources in the environment. Compared with fuel cells and lithium batteries in the prior art, the present invention can reduce the fuel carrying amount, and more importantly, can reduce the weight of the entire aircraft body, fully reduce energy consumption, and improve the mobility of the aircraft body.

[0030] In a specific embodiment, the electrode has a strip structure, preferably an electrolytic rod 15, one end of which is fixed at the head end position of the reaction chamber 7, and the other end extends towards the tail end of the reaction chamber 7 to fully expand the range of electrolysis of the water flow in the reaction chamber 7 and improve the rate of electrolysis of the water flow. Preferably, the length of the electrode is one-half to three-fourths of the length of the reaction chamber 7 along its traveling direction.

[0031] In a specific embodiment, the electronic ignition mechanism 16 is located at a position close to the head end of the reaction chamber 7, so that when it is necessary to emerge from the water, the entire aircraft body is kept in a state where the head section is upward and the tail end is downward, and the hydrogen-oxygen mixed gas in the reaction chamber 7 gathers at the top position of the reaction chamber 7, and then the electronic ignition mechanism 16 is used to ignite the hydrogen-oxygen mixed gas gathered at the top position of the reaction chamber 7. And preferably, the electronic ignition mechanism 16 is arranged at the central position of the reaction chamber 7, so as to evenly push the water flow below it as much as possible after the hydrogen-oxygen mixed gas explodes.

[0032] In a specific embodiment, a detection mechanism 13 for detecting the concentration of hydrogen and oxygen gases is further provided at a position near the head end of the reaction chamber 7. The detection mechanism 13 is electrically connected to the electronic ignition mechanism 16. When the electrolytic water mechanism 14 is started, the two-phase electrodes electrolyze water to generate hydrogen and oxygen. When the hydrogen and oxygen gases accumulate to a certain concentration and the corresponding value is detected by the detection mechanism 13, the detection mechanism 13 sends a signal to the electronic ignition mechanism 16 to trigger ignition.

[0033] In a specific embodiment, a nozzle 17 is coaxially connected to the injection port 8. The flow cross-section of the nozzle 17 gradually increases along the direction of the water flow. After the electronic ignition mechanism 16 ignites the hydrogen-oxygen mixed gas, it causes a violent combustion explosion. The shock wave generated by the explosion flushes the remaining water to the tail end of the reaction chamber 7, and then forms a jet from the injection port 8 and is amplified and ejected through the nozzle 17 to ensure that the ejected high-pressure water flow generates a reaction thrust on the aircraft body. Preferably, the aircraft body and the nozzle 17 are integrally formed.

[0034] In a specific embodiment, the part of the reaction chamber 7 connected to the injection port 8 has a conical structure 9, and its flow cross-section gradually decreases along the direction of the water flow. In combination with the structure of the nozzle 17 whose flow cross-section gradually increases along the direction of the water flow, the two form a Laval nozzle 17 structure. After the electronic ignition mechanism 16 ignites the hydrogen-oxygen mixed gas, it causes a violent combustion explosion. The shock wave generated by the explosion flushes the remaining water to the tail end of the reaction chamber 7. At this stage, the movement of the water flow follows the principle that "when a fluid moves in a pipe, the flow velocity is high at a small cross-section and low at a large cross-section". Limited by the gradually decreasing flow cross-section of the part of the reaction chamber 7 connected to the injection port 8, the water flow is continuously accelerated. When it reaches the injection port 8, the flow velocity has exceeded the speed of sound. However, a transonic fluid no longer follows the principle that "the flow velocity is high at a small cross-section and low at a large cross-section" during movement, but on the contrary, the larger the cross-section, the faster the flow velocity. Therefore, when the water flow flows into the nozzle 17 through the injection port 8, it actually plays a role in increasing the flow velocity of the water flow.

[0035] In a specific embodiment, the reaction chamber 7 is equipped with a water filling mechanism for filling it with water. The water filling mechanism includes a negative pressure pump 10 installed on the outside of the reaction chamber 7. A negative pressure suction tube 11 is connected between the negative pressure pump 10 and the reaction chamber 7. Preferably, the negative pressure suction tube 11 is a hose structure to facilitate the arrangement of components such as the negative pressure pump 10. A conduction valve 12 is provided on the negative pressure suction tube 11. When the aircraft body is ready to enter the water, the reaction chamber 7 is filled with water under the action of the negative pressure pump 10. Specifically, by turning on the negative pressure pump 10 and the conduction valve 12 to form a suction operation on the reaction chamber 7, a negative pressure state is formed in the reaction chamber 7, and external water flows into the reaction chamber 7 through the injection port 8, thereby increasing the weight of the aircraft body to facilitate immersion in water. Subsequently, the water electrolysis mechanism 14 is started to electrolyze water to produce a certain amount of hydrogen and oxygen mixed gas, so that the reaction chamber 7 is filled with a gas-liquid mixture. Through the water replenishment mechanism of the water electrolysis mechanism 14 and the negative pressure pump 10, rapid filling and charging can be achieved, the time required for repeated launches can be shortened, and the efficiency of mission execution can be improved.

[0036] Preferably, the conduction valve 12 is a ball valve, and a negative pressure suction port is opened on the outer wall of the reaction chamber 7. The ball valve is installed at the negative pressure suction port and connected to the negative pressure suction port. Preferably, the conduction valve 12 is an electronic valve, so that when the aircraft body is ready to enter the water, the conduction valve 12 can be controlled to open by electronic control, and the negative pressure pump 10 can be started to perform suction work on the reaction chamber 7.

[0037] Furthermore, a power supply battery 6 is provided on the outer wall of the reaction chamber 7, which is specifically installed at the top position of the outer wall of the reaction chamber 7, and the power supply battery 6 is located at the central axis of the aircraft body to balance the weight of the entire aircraft body and ensure its stability during travel. The power supply battery 6 is used to power the water electrolysis mechanism 14, the negative pressure pump 10, the electronic ignition mechanism 16 and the conduction valve 12, and preferably, the power supply battery 6 adopts a waterproof battery structure.

[0038] In a specific embodiment, the aircraft body is also provided with a ground effect wing 1 symmetrically distributed on both sides of the reaction chamber 7, and each end of the ground effect wing 1 away from the reaction chamber 7 is provided with a wing end plate 3, and the wing end plate 3 extends in the vertical direction. The preferred ground effect wing 1 and the wing end plate 3 are made of carbon fiber reinforced material and are connected to the aircraft body by bonding and fixing. By arranging the ground effect wing 1 and the wing end plate 3, the aircraft body can generate a ground effect during flight, and obtain a larger lift with relatively low energy consumption.

[0039] In a specific embodiment, a tail wing is further provided on the aircraft body. The tail wing includes a vertical tail wing 5 connected to the top of the tail end of the reaction chamber 7. A horizontal tail wing 4 is connected to the top of the vertical tail wing 5. Preferably, both the vertical tail wing 5 and the horizontal tail wing 4 are made of carbon fiber reinforced materials. The vertical tail wing 5 is connected to the aircraft body by an adhesive fixing method, and the horizontal tail wing 4 is connected to the vertical tail wing 5 by an adhesive fixing method. Under the action of the vertical tail wing 5 and the horizontal tail wing 4, the aircraft body can take off smoothly and quickly enter the low-altitude gliding state. Generally speaking, in the cross-medium aircraft disclosed in the present invention, a reaction force is generated by the ejected water flow to push the aircraft body to quickly float or take off. By setting the ground effect wing 1 and the wing end plate 3, the energy consumption is reduced by means of the ground effect, and a greater lift is obtained. And by setting the tail wing to provide stability and control force during flight, the aircraft body can smoothly enter the low-altitude gliding state.

[0040] Furthermore, a reaction chamber housing 2 is further provided on the aircraft body. The reaction chamber housing 2 covers the outer peripheral side of the reaction chamber 7 to wrap the reaction chamber 7, the negative pressure pump 10, the negative pressure suction pipe 11, and the parts of the electrolytic water mechanism 14 located outside the reaction chamber 7, playing a protective role. And the ground effect wing 1, the tail wing, etc. are all connected to the reaction chamber housing 2.

[0041] As a preference, in the cross-medium aircraft disclosed in the present invention, the reaction chamber 7, the electronic ignition mechanism 16, the electrolytic water mechanism 14, the negative pressure pump 10, the conduction valve 12, the negative pressure suction pipe 11, the reaction chamber housing 2, the ejection port 8, and the nozzle 17 are all arranged in the same longitudinal plane in the vertical direction to ensure the flight stability of the entire cross-medium aircraft.

[0042] Adaptations made according to actual needs are all within the protection scope of the present invention.

[0043] 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 exemplary embodiments, and without departing from the spirit or basic characteristics of the present invention, the present invention can be implemented in other specific forms. 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 included in the present invention. Any reference signs in the claims should not be regarded as limiting the claimed rights.

[0044] In the present invention, specific examples are used to illustrate the principle and implementation manner 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 manner and application scope. In summary, the content of this specification should not be construed as a limitation on the present invention.

Claims

1. A cross-media aircraft, characterized in that, It includes an aircraft body and a power mechanism for driving the aircraft body to fly across the medium; The power mechanism includes a reaction chamber opened on the aircraft body and used to store water, the tail end of the reaction chamber along the direction of its movement is provided with a nozzle for ejecting water flow, and the nozzle is directed toward the reaction chamber away from the direction of its movement; the head end of the reaction chamber along the direction of its movement is provided with a water electrolysis mechanism, and the water electrolysis mechanism is provided with electrodes of two phases both extending into the interior of the reaction chamber, and the two electrodes are distributed at intervals; the reaction chamber is provided with an electronic ignition mechanism for igniting the hydrogen-oxygen mixed gas.

2. The cross-media aircraft according to claim 1, wherein The electrode is in a strip-shaped structure, one end of which is fixed at the head end of the reaction chamber, and the other end of which extends toward the tail end of the reaction chamber.

3. The cross-media aircraft according to claim 2, characterized in that, The length of the electrode is one half to three quarters of the length of the reaction chamber along the direction of travel thereof.

4. The cross-medium aircraft according to claim 2 or 3, characterized in that, The electronic ignition mechanism is located in the reaction chamber near its head end.

5. The cross-media aircraft according to claim 4, characterized in that, A detection mechanism for detecting the concentration of hydrogen and oxygen gases is also provided in the reaction chamber near its head end, and the detection mechanism is electrically connected to the electronic ignition mechanism.

6. The cross-media aircraft according to claim 1, characterized in that The jet port is coaxially connected with a nozzle, and the flow cross section of the nozzle gradually increases along the direction in which the water jets out.

7. The cross-medium aircraft according to claim 6, characterized in that, The portion of the reaction chamber that is in communication with the injection port is in a conical structure, and its flow cross section gradually decreases along the direction in which the water flow is ejected.

8. The cross-media aircraft according to claim 1, wherein The reaction chamber is equipped with a water filling mechanism for filling it with water. The water filling mechanism includes a negative pressure pump installed outside the reaction chamber. A negative pressure suction pipe is connected between the negative pressure pump and the reaction chamber. A conduction valve is provided on the negative pressure suction pipe.

9. The cross-medium aircraft according to claim 1, wherein, The aircraft body is also provided with ground effect wing wings symmetrically distributed on both sides of the reaction chamber, and the end of each ground effect wing wing away from the reaction chamber is provided with a wing end plate, and the wing end plate extends in the vertical direction.

10. The cross-media aircraft according to claim 9, wherein, The aircraft body is also provided with a tail wing, which includes a vertical tail wing connected to the top of the tail end of the reaction chamber, and the top of the vertical tail wing is connected to a horizontal tail wing.

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