CN111806174B - An aircraft structure that can repeatedly enter and exit the water - Google Patents

Abstract

The invention discloses an aircraft structure capable of repeatedly entering and exiting water, comprising a fuselage, the fuselage is provided with a retractable wing and a rotatable tail, a fuel system is installed in the fuselage; The head member includes a gas storage tank, a cavitation device connected with the gas storage tank, and a pusher connected with the cavitation tank. The cavitation device includes an annular fixing portion with a front-end ventilation hole and a ventilation hole along the front-end. The moving control moving part, the pusher drives the control moving part to move to close or open the front vent hole, the head member also includes a vent ring hole connected with the air tank, and the pusher drives the annular fixed part to move to close the vent ring hole or on. The invention not only satisfies the air flight, but also does not produce excessive resistance to underwater diving, and can repeatedly enter and exit the water.

Description

An aircraft structure that can repeatedly enter and exit the water

technical field

The invention relates to the technical field of aircraft, in particular to an aircraft structure capable of repeatedly entering and exiting water.

Background technique

In recent years, with the rapid development and integration of aviation and navigation technologies, more and more countries have begun to study the structure of repeated entry and exit aircraft that can both fly in the air and navigate underwater. This kind of aircraft structure is a kind of aircraft structure that can autonomously cross the water-air interface and adapt to the two mediums of water and air and can navigate alternately for a long time. The application prospect of this type of aircraft structure is very broad. In civil use, it can be used in the maintenance of large bridges, first diving into the water to detect the state of the underwater structure, and then flying into the air to observe the situation on the water, and it can also fly. Dive into the water after a long distance, and perform search, rescue and salvage tasks for wrecked ships and aircraft.

The structure of the aircraft that repeatedly enters and exits the water has the ability to adapt to the water and air environment independently, and can cross the medium interface multiple times and continue to fly/navigate. control technology, etc. Since the density of air is 1/800 of the density of water, and the viscosity coefficient of air is 1/60 of that of water, the structure of the air vehicle and the structure of the underwater vehicle are very different in appearance. The structure of underwater vehicles is generally in the shape of a revolving body. In order to reduce the resistance of underwater navigation, there are no lift components such as wings or elastic wings, and wings are indispensable to air vehicles. The power system provides thrust for maneuvers such as pitch, yaw, roll, and crossing the water-air interface of the aircraft structure, and is a basic part of the overall system of the aircraft structure. There are two ways for the aircraft structure to enter the water. One is to turn off the power system after reaching the hovering state at a predetermined height in the air, and fall into the water under the action of gravity, which is called free water entry; the second is to gradually reduce the power to make the aircraft structure slow. Falling to the surface and below is called a controlled entry. Among them, the free entry into the water must face the impact of the water on the structure of the aircraft, which will lead to the failure of the internal instruments and even the damage of the structure of the aircraft. Controlled entry into the water in turn reduces the speed of the vehicle.

As far as the structure of the current aircraft that repeatedly enters and leaves the water is concerned, it is still not ideal in terms of entering and leaving the water, it is difficult to meet the requirements of repeated entry and exit, and the resistance is relatively large when diving underwater.

SUMMARY OF THE INVENTION

The present invention aims to solve one of the above-mentioned technical problems in the prior art at least to a certain extent. To this end, the embodiments of the present invention provide an aircraft structure that can repeatedly enter and exit the water, which not only satisfies the air flight, but also does not cause excessive resistance to underwater diving, and can repeatedly enter and exit the water.

The structure of the aircraft that can repeatedly enter and exit the water according to the embodiment of the present invention includes a fuselage, the fuselage is provided with a retractable wing and a rotatable tail, a fuel system is installed in the fuselage; The head member includes an air storage tank, a cavitation connected to the air storage tank, and a pusher connected to the cavitation, and the cavitation includes an annular fixing portion with a front-end ventilation hole and a ventilation hole along the front-end The moving control moving part, the pusher drives the control moving part to move to make the front vent hole close or open, the head member also includes a vent ring hole connected with the air tank, the pusher drives the annular fixing part to move to make the vent ring The hole is closed or open.

In an optional or preferred embodiment, the pusher includes a first hydraulic cylinder and a second hydraulic cylinder, the first hydraulic cylinder is connected to the control moving part to drive the control moving part to move, and the second hydraulic cylinder is connected to the annular fixing part to drive the annular fixing part Department moves.

In an optional or preferred embodiment, the control moving part has an opening and closing ring body matched with the front end vent hole, and the pusher drives the control moving part to move, so that the opening and closing ring body is placed in the front end vent hole or separated from the front end vent hole. stomata.

In an optional or preferred embodiment, the head member includes a fairing connected to the fuselage, the ventilation ring hole is arranged on one side of the head of the fairing, the annular fixing portion has a bottom end surface for closing the ventilation ring hole, and the pusher The annular fixing portion is driven to move, so that the bottom end face seals the vent ring hole or is away from the vent ring hole.

In an optional or preferred embodiment, the vent ring hole includes a plurality of head vent holes, each of which is annularly arranged.

In an optional or preferred embodiment, the fuel system includes a fuel storage chamber, a water intake and intake passage, a mixing chamber, and a combustion chamber. Both the fuel storage chamber and the water intake and intake passage communicate with the mixing chamber, and the mixing chamber communicates with the combustion chamber.

In an optional or preferred embodiment, the water inlet and air intake channels are arranged on the side walls of the fuselage.

In an optional or preferred embodiment, the fuel storage chamber is filled with nano-metal fuel.

In an optional or preferred embodiment, the gas storage tank is connected with a solenoid valve.

In an optional or preferred embodiment, a controller is provided in the fuselage, the fuel storage chamber is electrically connected to the controller, the solenoid valve is electrically connected to the controller, and the pusher is electrically connected to the controller.

Based on the above technical solution, the embodiments of the present invention have at least the following beneficial effects: the above technical solution, a head member is designed, and the cavitation of the head member can be jetted forward through the front vent hole, and the high-energy air jet is used in the head. Before the component touches the water, a gap is torn to form water cavitation, and the water enters the water smoothly along the channel of the gap on the water surface, which not only reduces the load impacting the water surface, but also does not need to reduce the speed; The gas is ejected from the ventilation ring holes, forming supercavitation in the water, thereby reducing the sailing resistance during the sailing process; the fuselage is provided with retractable wings and a rotatable tail, which enters the air medium from the water, and the wings can Expand and provide lift to make the flight altitude rise. The invention not only satisfies the flight in the air, but also does not produce excessive resistance to underwater diving, and can enter and exit the water repeatedly.

Description of drawings

In order to illustrate the technical solutions in the embodiments of the present invention more clearly, the following briefly describes the accompanying drawings that are used in the description of the embodiments. Obviously, the described drawings are only a part of the embodiments of the present invention, but not all of the embodiments, and those skilled in the art can also obtain other design solutions and drawings according to these drawings without creative work.

1 is a schematic structural diagram of an embodiment of the present invention when flying in the air;

Fig. 2 is the structural schematic diagram of the head member flying in the air in the embodiment of the present invention;

3 is a schematic structural diagram of the head member in the embodiment of the present invention when it enters water;

Fig. 4 is the structural representation when sailing in water according to the embodiment of the present invention;

FIG. 5 is a schematic structural diagram of the head member when sailing in water according to the embodiment of the present invention.

Detailed ways

This part will describe the specific embodiments of the present invention in detail, and the preferred embodiments of the present invention are shown in the accompanying drawings. Each technical feature and overall technical solution of the invention should not be construed as limiting the protection scope of the invention.

In the description of the present invention, it should be understood that orientation descriptions are involved, such as center, longitudinal, lateral, length, width, thickness, top, bottom, front, back, left, right, vertical, horizontal, top, bottom The orientation or positional relationship indicated by , inside, outside, clockwise, counterclockwise, axial, radial, circumferential, etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, and It is not indicated or implied that the indicated device or element must have a particular orientation, be constructed and operate in a particular orientation, and therefore should not be construed as limiting the invention.

In the description of the present invention, the meaning of several is one or more, the meaning of multiple is two or more, greater than, less than, exceeding, etc. are understood as not including this number, above, below, within, etc. are understood as including this number, unless otherwise There are clear and specific restrictions. In addition, if it is described that the first and second are only for the purpose of distinguishing technical features, it cannot be understood as indicating or implying relative importance, or implicitly indicating the number of indicated technical features or implicitly indicating the indicated technical features. the sequence relationship.

In the description of the present invention, unless otherwise clearly defined, terms such as setting, arranging, installing, connecting, connecting, fixing, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine that the above terms are used in the present invention in combination with the specific content of the technical solution. specific meaning in .

In the description of the present invention, unless otherwise expressly defined, the first feature is above or below the second feature, the first feature and the second feature may be in direct contact, or the first feature and the second feature may be in indirect contact through an intermediate medium. Also, the first feature is above/above/above the second feature, it may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is level higher than the second feature. The first feature is below/below/below the second feature, which can mean that the first feature is directly below or obliquely below the second feature, or just means that the level of the first feature is smaller than the second feature.

Referring to FIGS. 1 and 2 , a structure of an aircraft capable of repeatedly entering and exiting water includes a fuselage 11 and a head member 20 disposed on the head of the fuselage 11 .

The fuselage 11 is provided with a retractable wing 12 and a rotatable empennage 13 , and a fuel system is installed in the fuselage 11 . In addition, the fuselage 11 is a revolving body structure, and a tail nozzle 14 is provided at the rear of the fuselage 11 . The "head" and "tail" directions described in this embodiment are as shown in the figure. Specifically, the fuel system includes a fuel storage chamber 32, a water intake and intake passage 31, a mixing chamber 33 and a combustion chamber 34. Both the fuel storage chamber 32 and the water intake and intake passage 31 are connected to the mixing chamber 33, and the mixing chamber 33 is connected to the combustion chamber. 34 is connected, wherein the water inlet and air intake channels 31 are arranged on the side wall of the fuselage 11 . When sailing in the air, the wings 12 are unfolded. As shown in FIG. 1 , the air enters the mixing chamber 33 from the water inlet and air intake passages 31 , and is mixed with the fuel in the fuel storage chamber 32 in the mixing chamber 33 , and then burns in the combustion chamber 34 , in this embodiment, the material storage chamber 32 is filled with nano metal fuel, and the nano metal fuel has higher combustion efficiency under the same ratio, which means that under the premise of the same quality, the aircraft structure has a longer voyage, and The fuel can work both in the air and in the water. In addition, in this embodiment, the fuel system further includes a supplementary combustion chamber 35 , and the mixing chamber 33 is arranged in the middle of the combustion chamber 34 and the supplementary combustion chamber 35 .

3 , the head member 20 includes an air storage tank 27 , a cavitation device connected to the air storage tank 27 and a pusher 22 connected to the cavitation device. The cavitation device includes an annular fixing portion with a front-end ventilation hole 25 23 and a control moving part 24 that moves along the front-end vent hole 25, the pusher 22 drives the control-moving part 24 to move to close or open the front-end vent hole 25, and the head member 20 also includes a vent ring hole 26 connected with the air tank 27 The pusher 22 drives the annular fixing portion 23 to move to close or open the vent ring hole 26 .

In some of these embodiments, the pusher 22 includes a first hydraulic cylinder and a second hydraulic cylinder, the first hydraulic cylinder is connected to the control moving part 24 to drive the control moving part 24 to move, and the second hydraulic cylinder is connected to the annular fixed part 23 to drive The annular fixing portion 23 moves. Of course, in other embodiments, the pusher 22 may adopt a cylinder structure or other mechanical transmission components to drive the annular fixed portion 23 to move, and to drive the control moving portion 24 to move.

2 and 3, the control moving part 24 has an opening and closing ring body that matches with the front end vent hole 25, and the pusher 22 drives the control moving part 24 to move, so that the opening and closing ring body is placed in the front end vent hole 25 or disengaged Front vent hole 25 . It can be understood that the head member 20 shown in FIG. 2 is in flight in the air at this time, and the opening and closing ring is placed in the front-end ventilation hole 25, and the front-end ventilation hole 25 is closed; the head member shown in FIG. 3 . 20. At this time, the structure of the sailing body is ready to enter the water, and the opening and closing ring body is separated from the front vent hole 25. Specifically, the pusher 22 controls the moving part 24 to move toward the rear. At this time, the gas in the gas storage tank 27 can be sprayed from the front vent hole 25. Out, the air jet tore a gap before the head component contacts the water, forming water cavitation, and the head structure smoothly enters the water along the channel of the gap on the water surface, which not only reduces the load impacting the water surface, but also does not need to reduce the speed.

In addition, the head member 20 includes a fairing 21 connected to the fuselage 11 , a vent ring hole 26 is provided on one side of the head of the fairing 21 , the annular fixing portion 23 has a bottom end surface for closing the vent ring hole 26 , the pusher 22 The annular fixing portion 23 is driven to move, so that the bottom end face seals the vent ring hole 26 or is away from the vent ring hole 26 . In this embodiment, the ventilation ring hole 26 includes a plurality of head ventilation holes, and each head ventilation hole is annularly arranged. It can be understood that, in the head member 20 shown in FIG. 2 , the aircraft structure is flying in the air at this time, the bottom end face of the annular fixing portion 23 seals the ventilation ring hole 26 , and the ventilation ring hole 26 is closed; the head shown in FIG. 5 Component 20, at this time the sailing body structure is submerged in the water, the bottom end face is far away from the ventilation ring hole 26, the ventilation ring hole 26 is opened, and the gas in the air storage tank 27 can be ejected from the ventilation ring hole 26, thereby making the aircraft structure exceed the water. Cavitation sailing, as shown in Figure 4.

Preferably, the gas storage tank 27 is connected with a solenoid valve 41 , and the solenoid valve 41 is used to control the gas output state of the gas storage tank 27 . Further, the fuselage 11 is provided with a controller 42, the fuel storage chamber 32 is electrically connected to the controller 42, the solenoid valve 41 is electrically connected to the controller 42, the pusher 22 is electrically connected to the controller 42, and the For the control of the solenoid valve 41 , the fuel storage chamber 32 and the pusher 22 , the controller adopts the control method of the prior art.

As shown in Figures 1 and 2, when the aircraft structure is flying in the air, the opening and closing ring body is placed in the front vent hole 25, the front vent hole 25 is closed, the bottom end surface of the annular fixing portion 23 is sealed with the vent ring hole 26, and the vent ring The hole 26 is closed. At this time, the controller 42 unfolds the wing 12, the air enters the mixing chamber 33 from the water inlet and air intake passage 31, and is mixed with the fuel in the fuel storage chamber 32 in the mixing chamber 33, and then burns in the combustion chamber 34, and the nano-metal fuel The high-temperature and high-pressure gas is generated to provide power for the aircraft structure, the lift generated by the wing 12 balances the gravity of the aircraft structure, and the controller 42 is electrically connected to the tail 13, so that the tail 13 can be manipulated to make the aircraft structure realize deflection and pitch.

As shown in FIG. 3 , when the aircraft structure is ready to enter the water, the opening and closing ring body is separated from the front vent hole 25. Specifically, the pusher 22 controls the moving part 24 to move toward the tail. At this time, the gas in the air tank 27 is in the solenoid valve 41. Under the action of the air jet, a high-speed airflow is generated and ejected from the front vent hole 25. The air jet tears a gap before the head member contacts the water. During the water entry process, a gas cavity is formed and wrapped on the surface of the aircraft structure, so that the aircraft structure and the water body are formed. A certain gap is formed between them, thereby reducing the resistance, buffering and guiding the water entry, greatly reducing the impact load of the aircraft structure in the process of entering the water, avoiding the damage to the aircraft structure and the damage to its internal parts. During launching, the wings 12 are retracted at the same time.

As shown in FIGS. 4 and 5 , the bottom end face is away from the ventilation ring hole 26 , the ventilation ring hole 26 is opened, and the gas in the air storage tank 27 can be ejected from the ventilation ring hole 26 , so that the aircraft structure can sail in supercavitation in water. , at this time, the wing 12 has shrunk, the water enters through the water inlet channel 31, and reacts with the nano-metal fuel in the combustion chamber 34 to generate power, and the gas discharged from the fuel system will further generate ventilation supercavitation, wrapping the navigation Most of the aircraft can reduce the sailing resistance of the aircraft. When sailing underwater, if the aircraft structure needs to adjust the attitude, the sailing direction of the aircraft can also be controlled by manipulating the tail 13 .

After sailing in the water for a period of time, if you want to sail in the air, you can change the tail 13 to adjust the sailing attitude, and the pusher 22 moves the moving part 24 towards the tail, moves the annular fixed part 23 towards the tail, and retracts to prepare to enter the water At the same time, the solenoid valve is closed, and the ramjet power system provides power to make the aircraft structure part enter the air medium. After the aircraft structure completely enters the air medium for sailing, the wings 13 are unfolded. Provide lift, so that the flight height rises, the air enters the combustion chamber 34 from the water inlet channel 31 and reacts with the nano metal fuel, and the nano metal fuel provides power through combustion.

The embodiments of the present invention have been described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above-mentioned embodiments, and can also be made within the scope of knowledge possessed by those of ordinary skill in the technical field without departing from the purpose of the present invention. Various changes.

Claims (10)

1. An aircraft structure capable of repeatedly entering and exiting water, characterized in that: comprises that

The aircraft comprises a fuselage (11), wherein the fuselage (11) is provided with telescopic wings (12) and a rotatable tail wing (13), and a fuel system is installed in the fuselage (11); and

the head component (20) is arranged at the head part of the machine body (11), the head component (20) comprises an air storage tank (27), a cavitator connected with the air storage tank (27) and a pusher (22) connected with the cavitator, the cavitator comprises an annular fixing part (23) with a front end vent hole (25) and a control moving part (24) moving along the front end vent hole (25), the pusher (22) drives the control moving part (24) to move so as to enable the front end vent hole (25) to be closed or opened, the head component (20) further comprises a vent ring hole (26) connected with the air storage tank (27), and the pusher (22) drives the annular fixing part (23) to move so as to enable the vent ring hole (26) to be closed or opened.

2. The repeatable ingress and egress to and from the water craft structure of claim 1 wherein: the pusher (22) comprises a first hydraulic cylinder and a second hydraulic cylinder, the first hydraulic cylinder is connected with the control moving part (24) to drive the control moving part (24) to move, and the second hydraulic cylinder is connected with the annular fixing part (23) to drive the annular fixing part (23) to move.

3. The repeatable ingress and egress to and from the water craft structure of claim 2 wherein: the control moving part (24) is provided with an opening and closing ring body matched with the front end vent hole (25), and the pusher (22) drives the control moving part (24) to move so that the opening and closing ring body is arranged in the front end vent hole (25) or separated from the front end vent hole (25).

4. The repeatable ingress and egress to and from the water craft structure of claim 2 wherein: the head member (20) comprises a fairing (21) connected with the fuselage (11), the vent ring hole (26) is arranged on one side of the head of the fairing (21), the annular fixing part (23) is provided with a bottom end face used for closing the vent ring hole (26), and the pusher (22) drives the annular fixing part (23) to move so that the bottom end face seals the vent ring hole (26) or is far away from the vent ring hole (26).

5. The repeatable ingress and egress to and from the water craft structure of claim 4 wherein: the vent ring aperture (26) comprises a plurality of head vent apertures, each of which is annularly arranged.

6. The structure of an aircraft capable of repeated egress to and from the water according to any one of claims 1 to 5, wherein: the fuel system comprises a fuel storage chamber (32), a water inlet air inlet channel (31), a mixing chamber (33) and a combustion chamber (34), wherein the fuel storage chamber (32) and the water inlet air inlet channel (31) are communicated with the mixing chamber (33), and the mixing chamber (33) is communicated with the combustion chamber (34).

7. The repeatable ingress and egress to and from the water craft structure of claim 6 wherein: the water inlet air inlet channel (31) is arranged on the side wall of the machine body (11).

8. The repeatable ingress and egress to and from the water craft structure of claim 6 wherein: the fuel storage chamber (32) is filled with nano-metal fuel.

9. The repeatable ingress and egress to and from the water craft structure of claim 6 wherein: the air storage tank (27) is connected with an electromagnetic valve (41).

10. The repeatable ingress and egress to and from the water craft structure of claim 9 wherein: a controller (42) is arranged in the machine body (11), the fuel storage chamber (32) is electrically connected with the controller (42), the electromagnetic valve (41) is electrically connected with the controller (42), and the pusher (22) is electrically connected with the controller (42).

Images