Double-medium hybrid power variable-volume unmanned aerial vehicle structure

Abstract

The utility model provides a double-medium hybrid power variable-volume unmanned aerial vehicle structure which comprises an upper high-pressure air cabin, a lower high-pressure air cabin, an annular air bag, an elastic air bag and an air compressor, and the upper end and the lower end of the annular air bag are connected with the upper high-pressure air cabin and the lower high-pressure air cabin to define a closed inner cavity; an inner cavity of the annular air bag is communicated with the upper high-pressure air cabin and the lower high-pressure air cabin through valves respectively; an elastic air bag is arranged in the inner cavity and communicated with an air compressor installed in the upper high-pressure air cabin and an exhaust channel valve of the lower high-pressure air cabin, and high-pressure air in the elastic air bag is exhausted outwards through an exhaust channel to assist the aircraft in flying. According to the double-medium hybrid power unmanned aerial vehicle structure capable of changing the size, power is generated through movement cooperation of the light gas and the air, the light gas is compressed through negative pressure generated by positive pressure to control the aerial vehicle to ascend and descend, the power is further provided through the gas output by the positive pressure, and the unmanned aerial vehicle structure capable of changing the size is obtained. And the energy utilization efficiency can be better improved.

Description

Technical Field

[0001] The utility model relates to the technical field of flying devices, in particular to a structure of a double-medium composite power variable-volume unmanned aerial vehicle. Background Art

[0002] An aircraft refers to a device that flies within the atmosphere or in outer space. There are many types of aircraft, which are generally divided into aircraft, spacecraft, rockets, and missiles. Among them, aircraft can be divided into two categories: one relies on air static buoyancy to lift off, such as airships and balloons; the other relies on aerodynamic force to overcome its own gravity to lift off, such as airplanes and helicopters.

[0003] Aircraft that rely on air static buoyancy to lift off usually use hydrogen and helium as power sources. This type of aircraft structure usually includes an atmospheric pressure area and a high-pressure area. The compressed light gas in the high-pressure area is released into the atmospheric pressure area, and the decrease in gas density causes the aircraft to rise. When the air pump is started, the gas in the atmospheric pressure area is compressed and filled into the high-pressure area, and the increase in gas density reduces the buoyancy, causing the aircraft to descend. In the prior art, when compressing gas with an air pump, the energy consumed by the pump body is only for compressing the gas and cannot be fully utilized. Based on the device for generating negative pressure with positive pressure disclosed in the applicant's previous application CN219101736U, which utilizes the input positive pressure to generate negative pressure, and the compressed gas discharged from the hollow container and the gas output from the deflated elastic airbag can be further utilized as needed. It is considered that the structure and principle of generating negative pressure with positive pressure can be applied to aircraft that rely on air static buoyancy to lift off, compress light gases such as hydrogen / helium with the negative pressure generated by positive pressure, and further reasonably utilize the gas output by positive pressure, which can further improve the energy utilization efficiency.

[0004] At the same time, the volume of the aircraft in the prior art is usually not variable, and the volume of the device cannot be switched according to the working state of the light gas. A relatively large volume is required to set the atmospheric pressure area and the high-pressure area. Especially in the non-flight state, the device occupies too much volume, which is not conducive to handling and storage. If an external airbag is used to accommodate the gas, the airbag cannot be completely retracted and released, and is easily scratched and damaged.

[0005] Based on the above problems, a structure of a double-medium composite power variable-volume unmanned aerial vehicle is proposed, which generates power through the movement cooperation of two media, namely light gas and air, so that the energy utilization rate is higher and the energy utilization form is more diversified. Summary of the Utility Model

[0006] The utility model provides a structure of a double-medium composite power variable-volume unmanned aerial vehicle, which generates power through the movement cooperation of two media, namely light gas and air. The negative pressure generated by the positive pressure compresses the light gas to control the lifting of the aerial vehicle, and further uses the gas output by the positive pressure to provide power, which can better improve the energy utilization efficiency. The device can change its volume according to the working state of the light gas, making it more convenient for use and transportation.

[0007] To achieve the above technical purposes and effects, the utility model solves the above problems through the following technical solutions:

[0008] The structure of the double-medium composite power variable-volume unmanned aerial vehicle includes an upper high-pressure gas chamber and a lower high-pressure gas chamber that are relatively arranged and internally store high-pressure light gas. The upper and lower ends of the annular airbag are connected to the upper high-pressure gas chamber and the lower high-pressure gas chamber to enclose a closed inner cavity; the upper part of the annular airbag is connected to the upper high-pressure gas chamber through an annular airbag valve, and the inner cavity is connected to the lower high-pressure gas chamber through an inner cavity valve; an elastic airbag is arranged in the inner cavity, an air chamber is opened in the high-pressure gas chamber, an air compressor is installed in the air chamber, and the air compressor is connected to the elastic airbag through an air pressure valve at the bottom of the air chamber; an exhaust passage is opened in the lower high-pressure gas chamber, and the exhaust passage is connected to the elastic airbag through an exhaust valve. The high-pressure gas in the elastic airbag is discharged downward and / or laterally through the exhaust passage to obtain thrust; the annular airbag valve, the inner cavity valve, the air compressor, the air pressure valve, and the exhaust valve are connected to a control device through a circuit.

[0009] In the above solution, the compressed light gas stored in the upper high-pressure gas chamber and the lower high-pressure gas chamber enters the annular airbag and the inner cavity, and the density of the light gas decreases to provide the buoyancy for the aerial vehicle to rise. When descending, the air compressor inflates the elastic airbag, and the elastic airbag expands to press the light gas in the inner cavity back into the lower high-pressure gas chamber. When the elastic airbag deflates, the inner cavity becomes negative pressure, and the compressed gas discharged from the elastic airbag is discharged outward through the exhaust passage, and the aerial vehicle obtains the thrust in the required direction. Due to the pressure difference between the inner cavity and the atmospheric pressure, under the action of the atmospheric pressure, the upper high-pressure gas chamber and the lower high-pressure gas chamber approach each other, and the annular airbag is compressed, and the light gas is pressed back into the upper high-pressure gas chamber. The upper high-pressure gas chamber and the lower high-pressure gas chamber shrink into a flying saucer shape, the overall density of the aerial vehicle increases and the buoyancy decreases, and the aerial vehicle descends.

[0010] Further, the upper high-pressure gas chamber and the lower high-pressure gas chamber adopt a semi-flying saucer structure, the air chamber is an annular chamber opened downward from the top of the upper high-pressure gas chamber, and the top of the air chamber is provided with a cover body with an air intake through hole.

[0011] Further, the exhaust passage includes a main exhaust pipe connected to the exhaust valve, and a plurality of exhaust branch pipes are connected in parallel to the exhaust end of the main exhaust pipe. Each exhaust branch pipe is provided with a pipeline valve; the exhaust branch pipe includes a bottom exhaust pipe pointing downward and a side exhaust pipe pointing laterally along the circumferential array.

[0012] Furthermore, the annular airbag is a corrugated airbag extending longitudinally, and the annular airbag is made of a rubber material with surface tension. The corrugated airbag has good mechanical strength and has a good folding and storage effect in the non-inflated state.

[0013] Furthermore, the light gas filled in the upper high-pressure cabin and the lower high-pressure cabin is helium.

[0014] Furthermore, there are multiple annular airbag valves and inner cavity valves arranged in a circumferential array, and corresponding valve mounting holes are respectively opened on the upper high-pressure cabin and the lower high-pressure cabin.

[0015] Furthermore, the control device is internally provided with a power supply module and a wireless communication module, and the control device is installed in the air chamber opened at the top of the upper high-pressure cabin.

[0016] The advantages and effects of the present utility model are as follows:

[0017] 1. The structure of the double-medium composite power variable-volume unmanned aerial vehicle proposed by the present utility model uses light gas to provide the buoyancy for the aircraft to rise. When descending, the positive pressure output by the air compressor presses part of the light air back into the high-pressure cabin, causing a negative pressure in the inner cavity. Also, by utilizing the pressure difference between the inner cavity and the atmosphere, the annular airbag is compressed under the action of the atmospheric pressure, and another part of the light air is pressed back into the high-pressure cabin. The volume of the aircraft decreases and the density increases, and the aircraft descends under the action of gravity.

[0018] In the working process of this solution, the positive pressure has three functions. The first function is to expand the elastic airbag to press the light gas back into the lower high-pressure cabin; the second function is that the positive pressure gas discharged from the elastic airbag can provide the thrust in the required direction for the aircraft; the third function is that due to the discharge of the positive pressure gas from the elastic airbag, a negative pressure is formed in the inner cavity. The atmosphere causes the upper and lower high-pressure cabins to approach, and the light gas in the annular airbag is pressed back into the upper high-pressure cabin, changing the density and buoyancy of the device.

[0019] During one takeoff and landing working cycle of the aircraft, one positive pressure of the air compressor can not only control the volume of the light gas but also assist the aircraft in flying, better saving energy. This structure is a practice of the principle of generating negative pressure from positive pressure, which can make full use of the gas output by the air compressor and provide new ideas for the design of the aircraft.

[0020] 2. The present utility model adopts an overall structure with a middle telescopic part and upper and lower shells. When ascending, descending, and storing, the upper high-pressure cabin and the lower high-pressure cabin are retracted into the device, showing a flying saucer shape, with a small volume and being convenient for handling and storage; at the same time, the shell structure can effectively avoid damage to the airbag caused by scraping and impact. Description of the Drawings

[0021] Figure 1Schematic diagram of the structure of the dual-medium composite power variable-volume aircraft of the present utility model;

[0022] Figure 2 Schematic diagram of the initial state;

[0023] Figure 3 Schematic diagram of the floating flight state;

[0024] Figure 4 Schematic diagram of the positive pressure inflation state;

[0025] Figure 5 Schematic diagram of the negative pressure generation state;

[0026] Figure 6 Schematic diagram of the negative pressure compressing the light gas state;

[0027] Figure 7 Schematic diagram of the aircraft contraction and descent state.

[0028] Drawing number identification:

[0029] 1. Upper high-pressure air chamber, 2. Lower high-pressure air chamber, 3. Ring-shaped airbag, 4. Inner cavity, 5. Ring-shaped airbag valve, 6. Inner cavity valve, 7. Elastic airbag, 8. Air compressor, 9. Air pressure valve, 10. Exhaust valve, 11. Exhaust passage, 111. Main exhaust pipe, 112. Bottom exhaust pipe, 113. Side exhaust pipe, 12. Control device, 13. Air chamber, 14. Cover body, 15. Pipeline valve. Detailed implementation manners

[0030] The following further illustrates the present utility model in conjunction with embodiments, but the present utility model is not limited to these embodiments.

[0031] The structure of the dual-medium composite power variable-volume unmanned aircraft described in this embodiment is as shown in the attached Figure 1-3 figure, and includes an upper high-pressure air chamber 1 and a lower high-pressure air chamber 2 which are arranged opposite to each other up and down. The upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 adopt a rigid shell structure. The upper and lower ends of the ring-shaped airbag 3 are connected to the upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 to enclose a closed inner cavity 4. The ring-shaped airbag 3 is a corrugated airbag made of a rubber material with surface tension. The corrugated airbag has good mechanical strength and has a good folding and storage effect in the non-inflated state. The upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 adopt a semi-flying saucer structure, and in the contracted state of the ring-shaped airbag 3, the upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 are close to each other to form an overall flying saucer structure.

[0032] As shown in the attached Figure 2-6As shown, the upper part of the annular airbag 3 is connected to the upper high-pressure air cabin 1 through the annular airbag valve 5, and a mounting hole for installing the annular airbag valve 5 is provided at the bottom of the upper high-pressure air cabin 1. The inner cavity 4 is connected to the lower high-pressure air cabin 2 through the inner cavity valve 6, and a mounting hole for installing the inner cavity valve 6 is provided at the top of the lower high-pressure air cabin 2. The annular airbag valve 5 and the inner cavity valve 6 are multiple along the circumferential array, and a corresponding number of valve mounting holes are provided on the upper high-pressure air cabin 1 and the lower high-pressure air cabin 2. In the initial state of the aircraft, the upper high-pressure air cabin 1 and the lower high-pressure air cabin 2 are filled with high-pressure helium, and during the entire working process, the helium moves in the upper high-pressure air cabin 1, the lower high-pressure air cabin 2, the annular airbag 3, and the inner cavity 4, and there will be no escape loss. The dotted section in the figure represents helium, and the helium density is large in the densely dotted area and small in the sparsely dotted area.

[0033] Attached Figure 1 , 5 As shown, an air chamber 13 is provided on the top of the upper high-pressure air chamber 1, and an air compressor 8 and a control device 12 are installed in the air chamber 13. The output end of the air compressor 8 is connected to the elastic air bag 7 built into the inner cavity 4 through the air pressure valve 9 installed at the bottom of the air chamber 13. A curved cover 14 is arranged on the top of the air chamber 13. The cover 14 is snap-fitted to the air chamber 13 and has a plurality of air inlet holes. An exhaust channel 11 is provided in the lower high-pressure air chamber 2, and the exhaust channel 11 is connected to the elastic air bag 7 through the exhaust valve 10 installed on the top of the lower high-pressure air chamber 2. That is, the device inflates the elastic air bag 7 through the air compressor 8 through the air pressure valve 9, and deflates through the exhaust valve 10 and the exhaust channel 11. The high-pressure air discharged outward from the exhaust channel 11 can enable the aircraft to obtain thrust in the required direction.

[0034] As attached Figure 2-7 As shown, in the embodiment, the exhaust channel 1 includes a main exhaust pipe 111 connected to the exhaust valve 10, and the exhaust end of the main exhaust pipe 111 is connected in parallel with a plurality of exhaust branch pipes, each of which is equipped with a pipeline valve 15. In the embodiment, the exhaust branch pipes include a bottom exhaust pipe 112 pointing downward, and four side exhaust pipes 113 pointing to the side along a circumferential array. The gas discharged downward from the bottom exhaust pipe 112 can enable the device to obtain a buffer force when descending, and the gas discharged from the side exhaust pipe 113 can enable the device to obtain a lateral thrust to adjust the falling position.

[0035] The annular airbag valve 5, the inner cavity valve 6, the air compressor 8, the air pressure valve 9, the exhaust valve 10, and the pipeline valve 15 are connected to the control device 12. The control device 12 has a built-in power module and a wireless communication module. The control device 12 can be used to control the aircraft to enter different working states.

[0036] As attached Figure 2-7 As shown, the dual-medium composite power volume-changing unmanned aerial vehicle structure of this embodiment includes the following steps (the gas flow direction is shown by the solid arrow):

[0037] S1. Initial state. As shown in the appendix Figure 2 , all valves are in the closed state. The gas in the annular airbag 3, inner cavity 4, and elastic airbag 7 is discharged and in a compressed state. The upper high-pressure chamber 1 and the lower high-pressure chamber 2 are close to each other, and high-pressure helium gas is stored in the upper high-pressure chamber 1 and the lower high-pressure chamber 2.

[0038] S2. The aircraft ascends and flies. As shown in the appendix Figure 3 , the annular airbag valve 5 and the inner cavity valve 6 are opened. The compressed light gas in the upper high-pressure chamber 1 and the lower high-pressure chamber 2 respectively enters the annular airbag 3 and the inner cavity 4. The annular airbag 3 and the inner cavity 4 expand, and the density of the light gas decreases to provide the buoyancy for the aircraft to rise.

[0039] S3. When the aircraft is about to descend. As shown in the appendix Figure 4 , the air compressor 8 is started and the air pressure valve 9 is opened to inflate the elastic airbag 7, entering the positive pressure inflation state. The elastic airbag 7 expands and squeezes the light gas in the inner cavity 4, compressing the light gas back into the lower high-pressure chamber 2 through the inner cavity valve 6 (the expansion / contraction direction of the elastic airbag 7 is shown by the dotted arrow), and then the air pressure valve 9 and the inner cavity valve 6 are closed. At this time, positive pressure gas is filled in the elastic airbag 7, the overall density of the device increases, and the aircraft initially shows a descending trend.

[0040] S4. The positive pressure generates a negative pressure state. As shown in the appendix Figure 5 , the exhaust valve 10 is opened to deflate the elastic airbag 7. The compressed gas discharged from the deflation of the elastic airbag 7 is quickly ejected outward through the exhaust passage 11 to obtain thrust. The elastic airbag 7 deflates and shrinks to gradually reach the atmospheric pressure, and the air pressure P2 in the inner cavity 4 is less than the atmospheric pressure P1 to form a negative pressure. By controlling the device 12 to select the pipeline valve 15 to be opened, the gas discharged downward from the bottom exhaust pipe 112 can enable the device to obtain a buffering force during descent, and the gas discharged from the side exhaust pipe 113 can enable the device to obtain a lateral thrust to adjust the falling position.

[0041] S5. The aircraft contracts and descends state. As shown in the appendix Figure 6 , the air pressure P2 in the inner cavity 4 is negative pressure. Under the action of the atmospheric pressure, the upper high-pressure chamber 1 and the lower high-pressure chamber 2 approach, and the inner cavity 4 contracts, driving the light gas in the annular airbag 3 to be compressed back into the upper high-pressure chamber 1 through the annular airbag valve 5. Finally, the annular airbag valve 5 and the exhaust valve 10 are closed, and the device returns to the initial state and continues to descend, as shown in the appendix Figure 7 ;

[0042] In step S4, the elastic airbag 7 deflates to gradually form a negative pressure in the inner cavity 4. During this process, a pressure difference appears between the inner cavity 4 and the atmospheric pressure. In step S5, with the appearance of the pressure difference, a compressive force is applied to the upper high-pressure chamber 1 and the lower high-pressure chamber 2. Steps S4 and S5 are carried out synchronously. During this process, the light gases in the upper high-pressure chamber 1 and the lower high-pressure chamber 2 are in a compressed state. The density of the aircraft is greater than that of the air, and it is in a continuous descending state under the action of gravity.

[0043] 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 described embodiments. For those skilled in the art, various changes, modifications, substitutions, and variations of these embodiments still fall within the protection scope of the present invention without departing from the principle and spirit of the present invention.

Claims

1. Dual-medium composite power volume-changing unmanned aerial vehicle structure, characterized by: The invention comprises an upper high-pressure gas chamber (1) and a lower high-pressure gas chamber (2) which are arranged opposite to each other and contain a high-pressure light gas, and an annular air bag (3) is connected at the upper and lower ends thereof to the upper high-pressure gas chamber (1) and the lower high-pressure gas chamber (2) to form a closed inner cavity (4); the upper part of the annular air bag (3) is connected to the upper high-pressure gas chamber (1) via an annular air bag valve (5), and the inner cavity (4) is connected to the lower high-pressure gas chamber (2) via an inner cavity valve (6); The inner cavity (4) has an elastic airbag (7) built in, the high-pressure air cabin (1) has an air chamber (13), an air compressor (8) is installed in the air chamber (13), and the air compressor (8) is connected to the elastic airbag (7) via an air pressure valve (9) at the bottom of the air chamber (13); the lower high-pressure air cabin (2) has an exhaust passage (11), the exhaust passage (11) is connected to the elastic airbag (7) via an exhaust valve (10), and the high-pressure gas in the elastic airbag (7) is discharged downward and / or sideways through the exhaust passage (11) to obtain thrust; The annular airbag valve (5), the inner cavity valve (6), the air compressor (8), the air pressure valve (9), and the exhaust valve (10) are connected to the control device (12) through lines.

2. The dual-medium composite power volume-changeable unmanned aerial vehicle structure according to claim 1 is characterized by: The upper high-pressure air chamber (1) and the lower high-pressure air chamber (2) adopt a semi-flying saucer-shaped structure, and the air chamber (13) is an annular chamber opened downward from the top of the upper high-pressure air chamber (1). The top of the air chamber (13) is provided with a cover body (14) with an air intake hole.

3. The dual-medium composite power volume-changeable unmanned aerial vehicle structure according to claim 1 is characterized by: The exhaust passage (11) comprises a main exhaust pipe (111) connected to the exhaust valve (10), a plurality of exhaust branch pipes are connected in parallel to the exhaust end of the main exhaust pipe (111), and each exhaust branch pipe is provided with a pipeline valve (15); The exhaust branch pipes include a bottom exhaust pipe (112) pointing downward, and side exhaust pipes (113) pointing sideways along a circumferential array.

4. The dual-medium composite power volume-changeable unmanned aerial vehicle structure according to claim 1 is characterized by: The annular airbag (3) is a corrugated airbag extending longitudinally, and the annular airbag (3) is made of a rubber material with surface tension.

5. The dual-medium composite power volume-changeable unmanned aerial vehicle structure according to claim 1 is characterized by: The light gas filled in the upper high-pressure gas chamber (1) and the lower high-pressure gas chamber (2) is helium.

6. The dual-medium composite power volume-changeable unmanned aerial vehicle structure according to claim 1 is characterized by: The annular airbag valve (5) and the inner cavity valve (6) are arranged in a plurality along a circumferential array, and a corresponding number of valve installation holes are respectively provided on the upper high-pressure air chamber (1) and the lower high-pressure air chamber (2).

7. The dual-medium composite power volume-changeable unmanned aerial vehicle structure according to claim 1 is characterized by: The control device (12) has a built-in power module and a wireless communication module, and the control device (12) is installed in an air chamber (13) opened at the top of the upper high-pressure air chamber (1).

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