Double-medium hybrid power variable-volume unmanned aerial vehicle structure and working method thereof

Abstract

The invention provides a double-medium hybrid power variable-volume unmanned aerial vehicle structure and a working method thereof. The double-medium hybrid power variable-volume unmanned aerial vehicle structure 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 variable-volume unmanned aerial vehicle structure and the working method thereof, power is generated through movement cooperation of the two media of light gas and air, the light gas is compressed through negative pressure generated by positive pressure to control the aircraft to ascend and descend, power is further provided through the gas output by the positive pressure, and the unmanned aerial vehicle structure is more compact. And the energy utilization efficiency can be better improved.

Description

Technical Field

[0001] The invention relates to the technical field of flying devices, in particular to a dual-medium composite power volume-changeable unmanned aerial vehicle structure and a working method thereof. Background Art

[0002] Aircraft refers to a device that flies in the atmosphere or outside the atmosphere. There are many types of aircraft, usually divided into aircraft, spacecraft, rockets and missiles. Aircraft can be divided into two categories: one relies on the static buoyancy of air to rise, such as airships and balloons; the other relies on aerodynamics to overcome its own gravity to rise, such as airplanes and helicopters.

[0003] Aircraft that rely on the static buoyancy of air to rise usually use hydrogen and helium as power sources. The aircraft of this structure usually includes a normal pressure area and a high pressure area. The compressed light gas in the high pressure area is released into the normal pressure area, and the gas density decreases to make the aircraft rise. The air pump is started to compress the gas in the normal pressure area and fill it into the high pressure area. The gas density increases and the buoyancy decreases, causing the aircraft to descend. In the prior art, the gas is compressed by the air pump, and the energy consumed by the pump body is only to compress the gas, which cannot be fully utilized. Based on the device for generating negative pressure with positive pressure disclosed in the applicant's previous application CN219101736U, the positive pressure input is used to generate negative pressure, and the gas compressed and discharged in the hollow container and the gas output by the deflation of the elastic airbag can be further utilized as needed. It is believed that the structure and principle of generating negative pressure with positive pressure can be applied to aircraft that rely on the static buoyancy of air to rise, and the light gas such as hydrogen / helium is compressed by the negative pressure generated by the positive pressure, and the gas output by the positive pressure is further reasonably utilized, which can further improve the efficiency of energy utilization.

[0004] At the same time, the volume of the aircraft in the prior art is usually not changeable, and the volume of the device cannot be switched according to the working state of the light gas. A larger volume is required to set the normal pressure area and the high pressure area. Especially in the non-flying state, the device occupies too much volume, which is not conducive to transportation and storage. If an external airbag is used to contain the gas, the airbag cannot be fully retracted and is easily scratched and damaged.

[0005] Based on the above problems, a dual-medium composite power volume-changing unmanned aerial vehicle structure and its working method are proposed. Power is generated by the movement coordination of light gas and air, which makes energy utilization more efficient and makes energy utilization more diversified. Summary of the invention

[0006] The present invention provides a dual-medium composite power volume-changing unmanned aerial vehicle structure and a working method thereof, which generates power through the movement of two media, light gas and air, compresses the light gas by the negative pressure generated by the positive pressure to control the ascent and descent of the aircraft, 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 the volume according to the working state of the light gas, which is more convenient to use and transport.

[0007] In order to achieve the above technical objectives and the above technical effects, the present invention solves the above problems through the following technical solutions:

[0008] The structure of a dual-medium composite power unmanned aerial vehicle with a variable volume comprises an upper high-pressure air cabin and a lower high-pressure air cabin which are relatively arranged and have built-in high-pressure light gas, and the upper and lower ends of an annular airbag are connected to the upper high-pressure air cabin and the lower high-pressure air cabin to form a closed inner cavity; the upper part of the annular airbag is connected to the upper high-pressure air cabin through an annular airbag valve, and the inner cavity is connected to the lower high-pressure air cabin through an inner cavity valve; an elastic airbag is built in the inner cavity, an air chamber is set in the high-pressure air cabin, an air compressor is installed in the air chamber, and the air compressor is connected to the elastic airbag through the air pressure valve at the bottom of the air chamber; an exhaust channel is set in the lower high-pressure air cabin, and the exhaust channel is connected to the elastic airbag through the exhaust valve, and the high-pressure gas in the elastic airbag is discharged downward and / or sideways through the exhaust channel to obtain thrust; the annular airbag valve, inner cavity valve, air compressor, air pressure valve, and exhaust valve lines are connected to a control device.

[0009] In the above scheme, the compressed light gas stored in the upper and lower high-pressure air chambers enters the annular airbag and the inner cavity, and the density of the light gas decreases to provide buoyancy for the aircraft 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 air chamber. The elastic airbag is deflated to make the inner cavity negative pressure, and the elastic airbag discharges the compressed gas to the outside through the exhaust channel, and the aircraft obtains thrust in the required direction. Because there is a pressure difference between the inner cavity and the atmospheric pressure, under the action of atmospheric pressure, the upper and lower high-pressure air chambers are close to each other, the annular airbag is compressed, and the light gas is pressed back to the upper high-pressure air chamber. The upper and lower high-pressure air chambers shrink to form a flying saucer shape, the overall density of the aircraft increases, the buoyancy decreases, and the aircraft descends.

[0010] Furthermore, the upper high-pressure air cabin and the lower high-pressure air cabin adopt a semi-flying saucer-shaped structure, the air chamber is an annular chamber opened downward from the top of the upper high-pressure air cabin, and a cover body with an air inlet hole is arranged on the top of the air chamber.

[0011] Furthermore, the exhaust channel includes a main exhaust pipe connected to an exhaust valve, and a plurality of exhaust branch pipes are connected in parallel to the exhaust end of the main exhaust pipe, and each exhaust branch pipe is equipped with a pipeline valve; the exhaust branch pipes include a bottom exhaust pipe pointing downward, and side exhaust pipes pointing to the sides along a circular array.

[0012] Furthermore, the annular airbag is a longitudinally extending corrugated airbag, 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 a non-inflated state.

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

[0014] Furthermore, the annular airbag valve and the inner cavity valve are multiple and arranged in a circumferential array, and a corresponding number of valve installation holes are respectively provided on the upper high-pressure air chamber and the lower high-pressure air chamber.

[0015] Furthermore, the control device has a built-in power module and a wireless communication module, and the control device is installed in an air chamber opened on the top of the upper high-pressure gas cabin.

[0016] The working method of the dual-medium composite power volume-changing unmanned aerial vehicle structure comprises the following steps:

[0017] S1, initial state, all valves are closed, the gas in the annular airbag, inner cavity and elastic airbag is discharged in a compressed state, the upper high-pressure air chamber and the lower high-pressure air chamber are close to each other, and the high-pressure helium is stored in the upper high-pressure air chamber and the lower high-pressure air chamber;

[0018] S2, the aircraft is flying upward, the annular airbag valve and the inner cavity valve are opened, the compressed light gas in the upper high-pressure air chamber and the lower high-pressure air chamber enters the annular airbag and the inner cavity respectively, the annular airbag and the inner cavity are expanded, the density of the light gas is reduced, and the buoyancy of the aircraft is provided;

[0019] S3. When the aircraft is ready to descend, the air compressor is started, the air pressure valve is opened to inflate the elastic airbag, and the positive pressure inflation state is entered; the elastic airbag expands and squeezes the light gas in the inner cavity, and compresses the light gas back into the lower high-pressure air cabin through the inner cavity valve, and then the air pressure valve and the inner cavity valve are closed;

[0020] S4, positive pressure generates negative pressure state, the exhaust valve is opened to deflate the elastic airbag, the compressed gas discharged by the deflated elastic airbag is quickly ejected outward through the exhaust channel to obtain thrust, the elastic airbag is deflated and gradually shrinks to reach atmospheric pressure, and the air pressure P2 in the inner cavity is less than the atmospheric pressure P1 to form negative pressure;

[0021] S5. When the aircraft shrinks and descends, the air pressure P2 in the inner cavity is negative. Under the action of atmospheric pressure, the upper and lower high-pressure air cabins move closer together and the inner cavity shrinks, driving the light gas in the annular airbag to be compressed back into the upper high-pressure air cabin through the annular airbag valve. Then the annular airbag valve and the exhaust valve are closed. The light gases in the upper and lower high-pressure air cabins are in a compressed state, the volume of the aircraft shrinks, the density increases, and it descends under the action of gravity.

[0022] The advantages and effects of the present invention are:

[0023] 1. The dual-medium composite power volume-changing unmanned aerial vehicle structure and its working method proposed in the present invention use light gas to provide buoyancy for the aircraft to rise. When descending, the positive pressure output by the air compressor presses part of the light air back to the high-pressure cabin and creates a negative pressure in the inner cavity. The pressure difference between the inner cavity and the atmosphere is used to compress the annular airbag under the action of atmospheric pressure, and the other part of the light air is pressed back to the high-pressure cabin. The volume of the aircraft is reduced, the density is increased, and the aircraft descends under the action of gravity.

[0024] In the working process of this scheme, positive pressure produces three effects. The first effect is to expand the elastic airbag to press the light gas back into the lower high-pressure air chamber; the second effect is that the positive pressure gas discharged from the elastic airbag can provide thrust to the aircraft in the required direction; the third effect is that the elastic airbag discharges the positive pressure gas, causing negative pressure in the inner cavity. The atmospheric effect brings the upper and lower high-pressure air chambers closer, and the light gas in the annular airbag is pressed back into the upper high-pressure air chamber, changing the density and buoyancy of the device.

[0025] During a take-off and landing cycle of an aircraft, the positive pressure of the air compressor can not only control the volume of light gas, but also assist the flight of the aircraft and save 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 aircraft.

[0026] 2. The present invention adopts an integral structure with a telescopic middle part and upper and lower shells. When ascending, descending, or storing, the upper and lower high-pressure air chambers are retracted into a flying saucer shape, which is small in size and convenient for transportation and storage. At the same time, the shell-type structure can effectively avoid damage to the capsule caused by scratches and collisions. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the structure of the dual-medium composite power variable volume aircraft of the present invention;

[0028] Figure 2 Schematic diagram of the initial state;

[0029] Figure 3 This is a schematic diagram of the floating flight state;

[0030] Figure 4 It is a schematic diagram of positive pressure inflation state;

[0031] Figure 5 It is a schematic diagram of negative pressure generation state;

[0032] Figure 6 It is a schematic diagram of the compression state of light gas under negative pressure;

[0033] Figure 7 This is a schematic diagram of the aircraft in the retracted and descending state.

[0034] Figure number identification:

[0035] 1. Upper high-pressure air chamber, 2. Lower high-pressure air chamber, 3. Annular airbag, 4. Inner cavity, 5. Annular airbag valve, 6. Inner cavity valve, 7. Elastic airbag, 8. Air compressor, 9. Air compressor valve, 10. Exhaust valve, 11. Exhaust channel, 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 DESCRIPTION

[0036] The present invention will be further described below with reference to examples, but the present invention is not limited to these examples.

[0037] The dual-medium composite power structure of the unmanned aerial vehicle capable of changing volume is shown in the attached Figure 1-3 As shown, it includes an upper high-pressure air chamber 1 and a high-pressure air chamber 2 which are arranged relatively up and down, and the upper high-pressure air chamber 1 and the high-pressure air chamber 2 adopt a hard shell structure. The upper and lower ends of the annular airbag 3 are connected to the upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 to form a closed inner cavity 4. The annular 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 a non-inflated state. The upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 adopt a semi-flying saucer-shaped structure. When the annular airbag 3 is in a contracted state, the upper high-pressure air chamber 1 and the high-pressure air chamber 2 are close to the whole and present a flying saucer-shaped structure.

[0038] As attached Figure 2-6 As 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.

[0039] Attached Figure 1 , 5As 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.

[0040] 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.

[0041] 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.

[0042] As attached Figure 2-7 As shown, the working method of the dual-medium composite power volume-changing unmanned aerial vehicle structure includes the following steps (the gas flow direction is shown by the solid arrow):

[0043] S1, initial state, as attached Figure 2 As shown, all valves are in a closed state, the gas in the annular airbag 3, the inner cavity 4, and the elastic airbag 7 is discharged in a compressed state, the upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 are close to each other, and the high-pressure helium is stored in the upper high-pressure air chamber 1 and the lower high-pressure air chamber 2;

[0044] S2, the aircraft ascends, such as Figure 3 As shown, the annular airbag valve 5 and the inner cavity valve 6 are opened, and the compressed light gas in the upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 enter the annular airbag 3 and the inner cavity 4 respectively. The annular airbag 3 and the inner cavity 4 are expanded, and the density of the light gas is reduced to provide buoyancy for the aircraft to rise;

[0045] S3. When the aircraft is preparing to descend, Figure 4As shown, the air compressor 8 is started, the air pressure valve 9 is opened to inflate the elastic airbag 7, and enter the positive pressure inflation state; the elastic airbag 7 expands and squeezes the light gas in the inner cavity 4, and compresses the light gas back into the lower high-pressure air 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, the elastic airbag 7 is filled with positive pressure gas, the overall density of the device increases, and the aircraft begins to show a downward trend;

[0046] S4, positive pressure produces negative pressure state, such as Figure 5 As shown, the exhaust valve 10 is opened to deflate the elastic airbag 7, and the compressed gas discharged by the deflated elastic airbag 7 is quickly ejected outward through the exhaust channel 11 to obtain thrust, and the elastic airbag 7 is deflated and gradually shrinks to reach atmospheric pressure, and the air pressure P2 in the inner cavity 4 is less than the atmospheric pressure P1 to form a negative pressure; the pipeline valve 15 to be opened is selected by the control device 12, and 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;

[0047] S5, the aircraft is in the state of retracted descent, such as Figure 6 As shown, the air pressure P2 in the inner cavity 4 is negative pressure. Under the action of atmospheric pressure, the upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 are close to each other, and the inner cavity 4 contracts, driving the light gas in the annular airbag 3 to be compressed back into the upper high-pressure air chamber 1 through the annular airbag valve 5; finally, the annular airbag valve 5 and the exhaust valve 10 are closed to restore the device to its initial state and continue to descend, as shown in the attached figure. Figure 7 As shown;

[0048] In step S4, the elastic airbag 7 is deflated to gradually form a negative pressure in the inner cavity 4. During this process, a pressure difference occurs between the inner cavity 4 and the atmospheric pressure. As the pressure difference occurs, step S5 begins to provide compression force to the upper high-pressure air chamber 1 and the lower high-pressure air chamber 2. Steps S4 and S5 are performed simultaneously. During this process, the light gas in the upper high-pressure air chamber 1 and the lower high-pressure air chamber 2 is in a compressed state, the density of the aircraft is greater than that of air, and the aircraft is in a continuous descending state under the action of gravity.

[0049] The embodiments of the present invention are described in detail above with reference to 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 without departing from the principles and spirit of the present invention still fall within the scope of protection 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).

8. A working method of a dual-medium composite power volume-changing unmanned aerial vehicle structure, characterized in that: Applied to the dual-medium composite power volume-changeable unmanned aerial vehicle structure according to any one of claims 1 to 7, the method comprises: S1, initial state, all valves are in a closed state, the gas in the annular airbag (3), the inner cavity (4), and the elastic airbag (7) is discharged and is in a compressed state, the upper high-pressure air chamber (1) and the lower high-pressure air chamber (2) are close to each other, and high-pressure helium is stored in the upper high-pressure air chamber (1) and the lower high-pressure air chamber (2); S2, the aircraft is flying upward, the annular airbag valve (5) and the inner cavity valve (6) are opened, and the compressed light gas in the upper high-pressure air chamber (1) and the lower high-pressure air chamber (2) enter the annular airbag (3) and the inner cavity (4) respectively, the annular airbag (3) and the inner cavity (4) are expanded, and the density of the light gas is reduced to provide buoyancy for the aircraft to rise; S3, when the aircraft is ready to descend, the air compressor (8) is started, the air pressure valve (9) is opened to inflate the elastic airbag (7), and the positive pressure inflation state is entered; the elastic airbag (7) expands and squeezes the light gas in the inner cavity (4), and compresses the light gas back into the lower high-pressure air chamber (2) through the inner cavity valve (6), and then the air pressure valve (9) and the inner cavity valve (6) are closed; S4, the positive pressure generates a negative pressure state, the exhaust valve (10) is opened to deflate the elastic airbag (7), the compressed gas discharged by the deflated elastic airbag (7) is quickly ejected outward through the exhaust channel (11) to obtain thrust, the elastic airbag (7) is deflated and gradually shrinks to reach atmospheric pressure, and the air pressure P2 in the inner cavity (4) is less than the atmospheric pressure P1 to form a negative pressure; S5, the aircraft is in a state of contraction and descent, the air pressure P2 in the inner cavity (4) is negative, and under the action of atmospheric pressure, the upper high-pressure air chamber (1) and the lower high-pressure air chamber (2) are brought closer, and the inner cavity (4) contracts, driving the light gas in the annular air bag (3) to be compressed back into the upper high-pressure air chamber (1) through the annular air bag valve (5); then the annular air bag valve (5) and the exhaust valve (10) are closed, and the light gas in the upper high-pressure air chamber (1) and the lower high-pressure air chamber (2) are both in a compressed state, the volume of the aircraft is reduced, the density is increased, and the aircraft descends under the action of gravity.

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