CN113665795A

CN113665795A - Simple aerial aircraft and delivery vehicle

Info

Publication number: CN113665795A
Application number: CN202010400300.4A
Authority: CN
Inventors: 杨斌堂; 杨锦堂
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-05-13
Filing date: 2020-05-13
Publication date: 2021-11-19

Abstract

The invention provides an aerial simple aircraft and a carrier, which comprise a control device, a height adjusting assembly, a flight supporting shell and a driving mechanism, wherein the height adjusting assembly and the driving mechanism are both arranged on the flight supporting shell, the control device can control the height adjusting assembly to realize the height adjustment of the aircraft, and the control device can control the driving mechanism to realize the adjustment of the flight direction. The invention realizes the flight of the aircraft by adopting the gas change generator and the air-based driving mechanism, the driving mechanism can realize the driving under the action of the resilience force of the elastic cavity and the external atmospheric pressure, and can realize the driving only by the resilience force of the elastic cavity, thereby realizing the flight task of the aircraft and meeting the actual flight requirement.

Description

Simple aerial aircraft and delivery vehicle

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aerial simple aircraft and a delivery vehicle.

Background

With the rapid development of science and technology, people research and explore aircrafts more and more diversification, generalization and scientification. In the field of traditional fixed-wing airplanes and helicopters, fixed-wing airplanes are fast in speed, long in voyage and long in voyage time, but most fixed-wing airplanes cannot take off and land vertically and hover in the air, take off and land are limited by places, and flexibility is poor.

Unmanned aerial vehicle has become one of the most fierce nouns in industry in recent years, and in fields such as taking photo by plane, express delivery, search and rescue after calamity, data acquisition, building, unmanned aerial vehicle has obtained wide application, and in the industry fields such as police force, city management, agriculture, geology, weather, electric power, express delivery, survey and drawing, plant protection, spray insecticide, survey and drawing, patrol and move ahead, unmanned aerial vehicle is playing bigger and bigger effect. The total consumption amount of the unmanned aerial vehicle market is expected to be increased by times in the future, the growth potential of the commercial unmanned aerial vehicle market is larger, but most unmanned aerial vehicles have the defects of large noise, high power consumption, complex structure and the like.

Patent document CN1639500A discloses an aircraft with a plurality of lift rotors and thrust rotors, one for each motor, and one inverter for each motor. In order to provide an aircraft with a larger effective load, a connecting rod is arranged between engines, but the design consumes much power, the structure is not compact enough, and the structural design is unreasonable.

Disclosure of Invention

In view of the defects in the prior art, the invention aims to provide an aerial simple aircraft and a vehicle.

The invention provides an aerial simple aircraft, which comprises a control device, a height adjusting assembly, a flight supporting shell and a driving mechanism, wherein the height adjusting assembly is arranged on the control device;

the height adjusting assembly and the driving mechanism are both arranged on the flight supporting shell;

the control device can control the height adjusting assembly to realize the height adjustment of the aircraft;

the control device can control the driving mechanism to realize the adjustment of the flight direction and provide driving force for flight through the driving mechanism.

Preferably, the driving mechanism comprises an energy storage device shell, a first elastic cavity and a fluid conveying assembly, and comprises any one of the following structural forms:

-a third conduit, the energy storage device housing having a slider disposed therein, the slider dividing the interior of the energy storage device housing into a first receiving space in which the first resilient chamber is mounted and a second receiving space in which a fluid is contained; an inlet of the fluid conveying assembly is connected with the second accommodating space through a first pipeline, and an outlet of the fluid conveying assembly is connected with the first elastic cavity through a second pipeline; when the fluid conveying assembly is started to work, the fluid sequentially passes through the first pipeline, the fluid conveying assembly and the second pipeline and enters the first elastic cavity, so that the volume of the first elastic cavity is driven to be increased; one end of the third pipeline is connected with the first elastic cavity, and the other end of the third pipeline extends to the outside of the energy storage device shell;

-a third accommodation space is provided in the energy storage device housing, the third accommodation space being filled with a fluid, the first resilient chamber being mounted in the third accommodation space; an inlet of the fluid conveying assembly is connected with the third accommodating space through a fourth pipeline, and an outlet of the fluid conveying assembly is connected with the first elastic cavity through a fifth pipeline; and a sixth pipeline is arranged on the first elastic cavity, penetrates through the energy storage device shell and extends to the outside of the energy storage device shell.

Preferably, any one of the following structural forms is included:

-a first valve is arranged on the third line;

-a fourth valve is arranged on the sixth pipeline.

Preferably, any one of the following structural forms is included:

-further comprising a second valve through which the first containing space communicates with the outside, and a third valve through which the second containing space communicates with the outside; the sliding piece is in sliding sealing fit with the energy storage device shell, and a sealing piece is arranged between the sliding piece and the energy storage device shell;

-a fifth valve is arranged on the energy storage device housing, and the third accommodating space is communicated with the outside through the fifth valve.

Preferably, the fluid delivery assembly comprises any one of the following structures:

-comprising a pump body and an electric motor capable of driving the pump body in rotation, the control device being electrically connected to the electric motor and to the first or fourth valve;

the linkage rod is provided with a first connecting end and a second connecting end, the first connecting end extends into the fluid actuator and forms a fourth accommodating space with the fluid actuator, the second connecting end extends into the power actuator and forms a fifth accommodating space with the power actuator, a first driving body is arranged in the fifth accommodating space, the linkage rod can move between a first position and a second position, the space of the fourth accommodating space is minimum in the first position, and the space of the fourth accommodating space is maximum in the second position; the linkage rod can move from a first position to a second position under the driving of the first driving body; the linkage rod can move from the second position to the first position under the driving of the first driving body and/or the external atmospheric pressure;

-a drive carrier, a fixed bar, a fluid carrier and a second drive body, one end of the drive carrier extending into the interior of the fluid carrier and forming a sixth accommodation space with the fluid carrier, the other end of the drive carrier being a free end, the fixed bar being mounted in the interior of the drive carrier and forming a seventh accommodation space with the drive carrier, the second drive body being mounted in the seventh accommodation space, the drive carrier being movable between a third position in which the space of the sixth accommodation space is minimal and a fourth position in which the space of the sixth accommodation space is maximal; the driving carrier can move from the fourth position to the third position under the driving of the second driving body; the drive carrier is capable of moving from the third position to the fourth position under the urging of the second drive body and/or ambient atmospheric pressure;

-comprising a third driving body, an annular casing, a choke plug and a pushing assembly, both mounted inside the annular casing and dividing the inside of the annular casing into an eighth housing space, in which the third driving body is mounted, and a ninth housing space, the pushing assembly being movable between a fifth position, in which the space of the ninth housing space is maximum, and a sixth position, in which the space of the ninth housing space is minimum; the pushing assembly can move from the fifth position to the sixth position under the driving of the third driving body; the push assembly is movable from the sixth position to the fifth position under the urging of the third drive body and/or ambient atmospheric pressure.

Preferably, the second pipeline comprises any one of the following connection forms:

the second pipeline is connected with the first elastic cavity through the energy storage device shell and the sliding part in sequence; when the sliding piece slides, the second pipeline moves along with the sliding piece;

the second line is connected to the first elastic chamber in turn via the energy storage device housing.

Preferably, one or more first pressure sensors are arranged inside the energy storage device shell, and the first pressure sensors are electrically connected with the control device; and/or

A second pressure sensor is arranged on the outer surface or inside the first elastic cavity and is electrically connected with the control device;

wherein, the first pressure sensor and/or the second pressure sensor adopts a force variation type sensor or a strain type sensor.

Preferably, the height adjusting assembly comprises a gas change generator, a second elastic cavity and a seventh pipeline;

the gas change generator is connected with the second elastic cavity through a seventh pipeline;

the control device can control the gas change generator to generate gas according to the requirement of the aircraft and send the gas into the second elastic cavity through a seventh pipeline.

Preferably, the device further comprises a fluid manifold, the number of the driving mechanisms is multiple, and the third pipeline or the sixth pipeline on the driving mechanism is connected with the fluid manifold;

the fluid manifold extends out of a plurality of fluid branch pipes, and the fluid branch pipes are connected with the flight support shell and can spray fluid in the fluid manifold to the outside of the flight support shell so as to provide power for the flight of the flight support shell.

According to the vehicle provided by the invention, the vehicle is installed on the simple aerial vehicle and comprises a carrier and a functional load, wherein the carrier can carry a load;

the control device can control the functional load to move to complete loading and unloading of the carried object.

Compared with the prior art, the invention has the following beneficial effects:

1. the invention adopts the gas change generator and the fluid-based driving mechanism to realize the flight of the aircraft, the driving mechanism can realize the working state under the action of the resilience force of the elastic cavity and the external atmospheric pressure, and can realize the working state only by depending on the resilience force of the elastic cavity, and the flow velocity or the flow of the fluid is adjusted, so that the flight task of the aircraft is realized by taking the fluid injection as the driving force, thereby meeting the requirement of actual flight.

2. The invention adopts a plurality of driving mechanisms which can be symmetrically arranged, can ensure the balance of the aircraft, can still ensure the normal flight of the aircraft when the individual driving mechanism breaks down, and improves the flight stability of the aircraft.

3. The spraying through holes in the flight supporting shell can be arranged into holes with single holes, multiple holes and arrays according to the structural surface type of the aircraft, or the combination of the holes with single holes, multiple holes and arrays can meet the requirements for adjusting the flight speed, the flight direction and the in-situ adjustment direction, and the structural surface type and the holes are flexibly and variously arranged correspondingly and have strong practicability.

4. According to the invention, the aperture of the injection through holes can be set to be small, and the injection through holes are densely distributed on the surface of the flight support shell, so that the small-flow dense injection of a plurality of injection through holes is realized, that is, the flight optimization combined power of the aircraft can be realized, and on the other hand, the fluid injection force is uniformly dispersed on the surface of the flight support shell, so that the injection noise is reduced, and the uniform injection is realized.

5. The invention has the advantages of no power consumption in the flying pushing process, stable energy output, less power consumption and strong stability.

6. The invention realizes the height adjustment of the aircraft by adopting the gas change generator and combining the second elastic cavity, and can flexibly adjust according to the actual load of the aircraft.

7. According to the invention, accurate fluid input and output adjustment is realized by adopting a plurality of flowmeters or pressure sensors, the stability of the device in an initial state and a working state is improved, and the practicability is strong.

8. The pipeline connected with the elastic cavity is of a flexible structure, so that the elastic cavity can move in a size-changing mode, and the practicability is high.

9. The fluid in the invention preferably adopts air, the driving force is realized through the circular flow of the air in the movement process, the external structure has no rotating part, the external environmental interference factors are less during flying, and the invention has stronger environmental adaptability.

10. The flight support shell can adopt structures such as shuttle type and butterfly type, and the resistance in the flight process is reduced.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic structural view of an aircraft according to the invention;

FIG. 2 is a schematic structural view of a flight support housing of the present invention;

FIG. 3 is a schematic structural view of the driving mechanism of the present invention without the sliding member;

FIG. 4 is a schematic view of the driving mechanism with the control device according to the present invention;

FIG. 5 is a schematic structural diagram of a first pressure sensor and a second pressure sensor according to the present invention;

FIG. 6 is a schematic structural view of the driving mechanism of the present invention with less fluid in the elastic cavity when the sliding member is used;

FIG. 7 is a schematic view of the structure of the present invention when the sliding member is used to contain a large amount of fluid in the elastic chamber;

FIG. 8 is a schematic structural view of a spherical housing of an energy storage device in a driving mechanism;

FIG. 9 is a schematic view of a flight support housing of the present invention with spray through holes;

FIG. 10 is a schematic diagram of a variation of the fluid delivery assembly;

FIG. 11 is a schematic structural view of another variation of a fluid delivery assembly;

fig. 12 is a schematic structural view of yet another variation of the fluid delivery assembly.

The figures show that:

fifth valve 18 injection through-hole 37 of energy storage device housing 1

First elastic cavity 2 control device 19 fluid actuator 38

Slider 3 first pressure sensor 20 power actuator 39

First accommodation space 4 second pressure sensor 21 flight support housing 40

Fluid delivery assembly 5 linkage rod 22 drive carrier 41

Second accommodation space 6 first connection end 23 fixing rod 42

Fluid carrier 43 of second connection end 24 of first pipeline 7

Sixth accommodation space 44 of fourth accommodation space 25 of second pipeline 8

Fifth receiving space 26 and seventh receiving space 45 of third pipeline 9

First valve 10, first driving body 27 and second driving body 46

Third driving body 47 of the height adjusting assembly 30 of the second valve 11

Third valve 12 gas change generator 31 annular housing 48

Third accommodation space 13 second elastic cavity 32 plug 49

Fourth line 14 seventh line 33 drive mechanism 50

Fifth pipeline 15 fluid manifold 34 push assembly 51

Eighth receiving space 52 of fluid branch 35 of sixth line 16

The ninth accommodation space 53 of the fourth valve 17 and the branch control valve 36

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

The invention provides an aerial simple aircraft, which comprises a control device 19, a height adjusting assembly 30, a flight supporting shell 40 and a driving mechanism 50, wherein the height adjusting assembly 30 and the driving mechanism 50 are both arranged on the flight supporting shell 40, the control device 19 can control the height adjusting assembly 30 to realize the height adjustment of the aircraft, and the control device 19 can control the driving mechanism 50 to realize the adjustment of the flight direction and provide driving force for flight through the driving mechanism 50, as shown in fig. 1.

Further, as shown in fig. 1, the height adjusting assembly 30 includes a gas change generator 31, a second elastic cavity 32 and a seventh pipeline 33, the gas change generator 31 is connected to the second elastic cavity 32 through the seventh pipeline 33, the control device 19 can control the gas change generator 31 to operate according to the demand of the aircraft, in a preferred example, the gas generated by the gas change generator 31 is hydrogen, and when the aircraft needs to be lifted, the control device 19 controls the gas change generator 31 to generate hydrogen and send the hydrogen into the second elastic cavity 32 through the seventh pipeline 33; the second elastic cavity 32 is provided with a gas discharge valve, and when the aircraft needs to be lowered, the control device 19 controls the gas discharge valve to realize the discharge of hydrogen in the second elastic cavity 32 according to the height required to be lowered so as to achieve the purpose of controlling the lifting of the aircraft.

It should be noted that the gas change generator 31 may be a device that generates other gas having a density lower than that of air, in addition to the hydrogen gas, and may implement the present invention. In particular, the gas change generator 31 can be implemented by means of a device for producing gas by chemical reaction and controlled by the control device 19, or by means of physical storage, such as high-pressure gas or liquefied gas, and in a preferred embodiment, by using high-pressure helium gas, which is lighter than air and inert gas and can be used to enable the device to fly to a higher altitude; in one variation, the hydrogen is liquefied and stored in a gas change generator, and when in use, the liquefied hydrogen is released and vaporized to release gaseous hydrogen, so that the control of the height of the aircraft is realized; when the hydrogen is cooled, the buoyancy of the device can be reduced, and the flying height of the device can be reduced.

Specifically, as shown in fig. 1, the flight support device further includes a fluid manifold 34, the number of the driving mechanisms 50 is multiple, the third pipeline 9 or the sixth pipeline 16 on the driving mechanism 50 is connected to the fluid manifold 34, the fluid manifold 34 collects the fluid in each driving mechanism 50, the fluid manifold 34 is distributed around the inner wall of the flight support housing 40, it should be noted that the fluid in the present invention is preferably air, the fluid manifold 34 extends out of a plurality of fluid branched pipes 35, and the plurality of fluid branched pipes 35 are connected to the flight support housing 40 and can spray the fluid in the fluid manifold 34 to the outside of the flight support housing 40 so as to provide power for the flight of the aircraft.

Specifically, in order to ensure the stable flight of the aircraft, the driving mechanisms 50 are symmetrically arranged in the flight supporting shell 40, so that the whole aircraft is balanced around and can fly in a linear track manner, and the influence on the flight efficiency caused by the fact that the weights of the two sides of the height adjusting assembly 30 are different and the flight tracks are curved is avoided.

In practical applications, the injection port of the fluid branch pipe 35 may extend to the outside of the flight support housing 40, or a plurality of injection through holes 37 may be uniformly or non-uniformly arranged on the outer surface of the flight support housing 40, as shown in fig. 9, the injection end of the fluid branch pipe 35 is connected to the end of the injection through hole 37 extending to the inner wall of the flight support housing 40, so as to discharge the fluid from the plurality of injection through holes 37, and further provide power for the flight of the aircraft.

Further, in a preferred embodiment, the fluid branch pipe 35 is provided with a branch pipe control valve 36, the control device 19 can control the opening and closing of the branch pipe control valve 36, the branch pipe control valve 36 of the injection port facing the flight direction is controlled to be closed by the aircraft flight direction control device 19, the branch pipe control valve 36 of the injection port opposite to the flight direction is opened, and when the flight direction needs to be adjusted, the control device 19 controls the injection ports in other directions to be opened or closed, so as to realize the flight function of turning.

Furthermore, the arrangement of the ejection through holes 37 on the flight support housing 40 may have various structural arrangement forms, for example, the aperture of the ejection through holes 37 is set to be a small aperture, and the surface of the flight support housing 40 is densely arranged, so that the small-flow dense ejection of the plurality of ejection through holes 37 is realized, that is, the flight driving force of the aircraft can be realized, and on the other hand, the fluid ejection force is uniformly dispersed on the surface of the flight support housing 40, so that the ejection noise is reduced, and the uniform ejection is realized.

Specifically, as shown in fig. 3 and 6, the driving mechanism 50 includes an energy storage device housing 1, a first elastic cavity 2, and a fluid delivery assembly 5, wherein the energy storage device housing 1 can adopt various structural forms according to practical applications, such as those shown in fig. 7 and 8.

Further, in a preferred embodiment, as shown in fig. 4, the fluid delivery assembly 5 includes a pump body and a motor, and the motor can drive the pump body to rotate so as to replenish the fluid in the first elastic cavity 2. In a variation, as shown in fig. 10, the fluid conveying assembly 5 includes a linkage rod 22, a fluid actuator 38, and a power actuator 39, the linkage rod 22 is provided with a first connection end 23 and a second connection end 24, the first connection end 23 extends into the fluid actuator 38 and forms a fourth accommodation space 25 with the fluid actuator 38, the second connection end 24 extends into the power actuator 39 and forms a fifth accommodation space 26 with the power actuator 39, the fifth accommodation space 26 is provided with a first driving body 27, the linkage rod 22 is capable of moving between a first position where the space of the fourth accommodation space 25 is minimum and a second position where the space of the fourth accommodation space 25 is maximum; when the fifth accommodating space 26 is a closed space, the linkage rod 22 can move from the second position to the first position under the driving of the first driving body 27, and/or the linkage rod 22 can move from the second position to the first position under the driving of the first driving body 27 and/or the external atmospheric pressure, wherein the eighth pipeline 28 is connected with the first elastic cavity 2, and the ninth pipeline 29 is connected with the fluid, so that the fluid in the first elastic cavity 2 can be replenished.

Further, in another modified example, as shown in fig. 11, the fluid delivery module 5 includes a driving carrier 41, a fixing rod 42, a fluid carrier 43, and a second driving body 46, one end of the driving carrier 41 extends into the fluid carrier 43 and forms a sixth receiving space 44 with the fluid carrier 43, the other end of the driving carrier 41 is a free end, the fixing rod 42 is installed inside the driving carrier 41 and forms a seventh receiving space 45 with the driving carrier 41, the second driving body 46 is installed in the seventh receiving space 45, the fixing rod 42 is fixed, the driving carrier 41 is capable of moving along the fixing rod 42 between a third position and a fourth position, in the third position, the space of the sixth receiving space 44 is minimum, and in the fourth position, the space of the sixth receiving space 44 is maximum; the drive carrier 41 can be moved from the fourth position to the third position or from the third position to the fourth position under the urging of the second driving body 46; the seventh receiving space 45 is a closed space, and the driving carrier 41 can move from the third position to the fourth position under the driving of the second driving body 46 and/or the external atmospheric pressure, wherein the sixth receiving space 44 is respectively provided with a pipeline connected with the first elastic cavity 2 and a pipeline connected with the fluid, and the fluid in the first elastic cavity 2 can also be supplemented. In still another modified example, as shown in fig. 12, the fluid transfer assembly 5 includes a third driving body 47, an annular housing 48, a stopper 49, and a pushing assembly 51, the stopper 49 and the pushing assembly 51 are both installed inside the annular housing 48 and divide the inside of the annular housing 48 into an eighth accommodating space 52 and a ninth accommodating space 53, the third driving body 47 is installed in the eighth accommodating space 52, the pushing assembly 51 is movable between a fifth position in which the space of the ninth accommodating space 53 is maximum and a sixth position in which the space of the ninth accommodating space 53 is minimum; the pushing assembly 51 can move from the fifth position to the sixth position or from the sixth position to the fifth position under the urging of the third driving body 47; the eighth accommodating space 52 is a closed space, the pushing assembly 51 can move from the sixth position to the fifth position under the driving of the third driving body 47 and/or the external atmospheric pressure, and the ninth accommodating space 53 is respectively provided with a pipeline connected with the first elastic cavity 2 and a pipeline connected with the fluid, so that the fluid in the first elastic cavity 2 can be supplemented.

Further, in a preferred embodiment, as shown in fig. 4, the first elastic cavity 2 is an elastic capsule, the control device 19 is electrically connected to the motor, and the control device 19 can control the motor to start or stop as required.

Specifically, as shown in fig. 5, one or more first pressure sensors 20 are disposed inside the energy storage device housing 1, and/or a second pressure sensor 21 is disposed on an outer surface of the first elastic cavity 2, and the first pressure sensor 20 and/or the second pressure sensor 21 are force-variable sensors or strain-variable sensors.

Further, as shown in fig. 5, the first pressure sensor 20 and the second pressure sensor 21 are electrically connected to the control device 19, respectively, and the first pressure sensor 20 and the second pressure sensor 21 can transmit detected pressure information to the control device 19, respectively, and can determine the pressure in the first elastic chamber 2.

Specifically, as shown in fig. 5, the first pressure sensor 20 and/or the second pressure sensor 21 are thin film strain sensors, in a preferred example, the first pressure sensor 20 is mounted on the inner surface of the energy storage device housing 1, and when the first elastic cavity 2 presses the first pressure sensor 20, the first pressure sensor 20 sends pressure sensing information to the control device 19 so as to obtain pressure information of the first elastic cavity 2, so that the control device 19 outputs control information; in a variation, the second pressure sensor 21 is a film-type pressure sensor, and can be stretched and adhered to the outside of the first elastic cavity 2, and when the first elastic cavity 2 expands or contracts, the second pressure sensor 21 is stretched along with the first elastic cavity 2, and can transmit the sensed pressure change information to the control device 19 to realize pressure monitoring; in another variation, the second pressure sensor 21 is disposed inside the first elastic cavity 2, and the second pressure sensor 21 can monitor the pressure inside the first elastic cavity 2 in real time and transmit pressure information to the control device 19, so that the control device 19 monitors the pressure inside the first elastic cavity 2, and then outputs a control instruction.

In particular, the invention is described below by means of two structural embodiments of the drive mechanism 50:

the first implementation mode comprises the following steps:

as shown in fig. 6 and 7, the driving mechanism 50 according to the present invention includes a third pipeline 9, a sliding member 3 is disposed in the energy storage device housing 1, the sliding member 3 divides the interior of the energy storage device housing 1 into a first accommodating space 4 and a second accommodating space 6, the first elastic cavity 2 is installed in the first accommodating space 4, and the second accommodating space 6 is filled with a fluid; the inlet of the fluid conveying assembly 5 is connected with the second accommodating space 6 through a first pipeline 7, and the outlet of the fluid conveying assembly 5 is connected with the first elastic cavity 2 through a second pipeline 8; when the fluid conveying assembly 5 is started to work, the fluid sequentially passes through the first pipeline 7, the fluid conveying assembly 5 and the second pipeline 8 and enters the first elastic cavity 2, so that the volume of the first elastic cavity 2 is driven to be increased; one end of the third pipeline 9 is connected with the first elastic cavity 2, and the other end of the third pipeline 9 extends to the outside of the energy storage device shell 1.

Specifically, as shown in fig. 6, in a preferred embodiment, a first valve 10 is disposed on the third pipeline 9, the control device 19 is electrically connected to the first valve 10, the control device 19 can control the opening and closing of the first valve 10 at any time according to actual needs, and can adjust the opening degree of the first valve 10 according to needs to meet the flow rate or flow rate of the fluid to be removed.

Specifically, as shown in fig. 6, the present invention further includes a second valve 11 and a third valve 12, the first accommodating space 4 is communicated with the outside through the third valve 12, the inside of the first accommodating space 4 can be evacuated through the third valve 12, the second accommodating space 6 is communicated with the outside through the second valve 11, the second accommodating space 6 is replenished with fluid to the inside through the second valve 11, the second valve 11 and the third valve 12 are electrically connected to a control device 19, and the control device 19 can control the second valve 11 and the third valve 12 to open and close, respectively.

Specifically, as shown in fig. 6, in a preferred embodiment, the second pipeline 8 and the third pipeline 9 respectively adopt a flexible structure, and when the first elastic cavity 2 becomes larger in volume, smaller in volume, or moves, because the second pipeline 8 and the third pipeline 9 have a margin in the length connecting with the first elastic cavity 2 and are of a flexible structure, the movement of the first elastic cavity 2 is not affected; in a variation, the second pipeline 8 and the third pipeline 9 are respectively of a rigid structure, and the present invention can be realized.

Specifically, as shown in fig. 6, in a preferred example, the elastic pressure measuring device further includes a first flow meter and a second flow meter, the first flow meter is mounted on the first pipeline 7, the second flow meter is mounted on the third pipeline 9, the first flow meter and the second flow meter are respectively electrically connected to the control device 19, the first flow meter and the second flow meter can respectively transmit detected flow information of the fluid to the control device 19 to obtain volumes of the fluid in the first elastic cavity 2 and the second accommodating space 6, so that the volume monitoring of the first elastic cavity 2 is realized, that is, pressure information inside the first elastic cavity 2 can be known, and the control device 19 further outputs control information.

Specifically, as shown in fig. 6, the sliding member 3 is in sliding sealing engagement with the energy storage device housing 1, and a sealing member, such as a sealing ring, and a rubber sealing gasket, are disposed between the sliding member 3 and the energy storage device housing 1.

Specifically, as shown in fig. 6, the second pipeline 8 is provided with a first check valve, and when the pump body stops rotating, the fluid in the first elastic cavity 2 can be prevented from flowing back into the second accommodating space 6 through the pump body due to the arrangement of the first check valve.

Specifically, in a preferred embodiment, as shown in fig. 6, the second pipeline 8 is connected to the first elastic cavity 2 through the energy storage device housing 1 and the sliding member 3 in sequence; when the sliding part 3 slides, the second pipeline 8 moves along with the sliding part 3, the second pipeline 8 has a length allowance, the sliding part 3 cannot be subjected to the resistance of the second pipeline 8 when sliding, and the connecting part of the second pipeline 8 and the sliding part 3 is in sealing connection. In one variation, the second line 8 is connected to the first elastic chamber 2 via the energy storage device housing 1 in sequence.

Embodiment 2:

as shown in fig. 3, in another structural embodiment of the driving mechanism 50 of the present invention, a third accommodating space 13 is provided in the energy storage device housing 1, the third accommodating space 13 is filled with a fluid, and the first elastic cavity 2 is installed in the third accommodating space 13; the inlet of the fluid conveying assembly 5 is connected with the third accommodating space 13 through a fourth pipeline 14, and the outlet of the fluid conveying assembly 5 is connected with the first elastic cavity 2 through a fifth pipeline 15; a sixth pipeline 16 is arranged on the first elastic cavity 2, and the sixth pipeline 16 penetrates through the energy storage device shell 1 and extends to the outside of the energy storage device shell 1.

Specifically, as shown in fig. 3, a fourth valve 17 is disposed on the sixth pipeline 16, the fourth valve 17 is electrically connected to a control device 19, and the control device 19 can control the opening and closing of the fourth valve 17.

Specifically, as shown in fig. 3, a fifth valve 18 is disposed on the energy storage device housing 1, the third accommodating space 13 is communicated with the outside through the fifth valve 18, the fifth valve 18 is electrically connected to a control device 19, and the control device 19 can control the opening and closing of the fifth valve 18.

Further, as shown in fig. 3, the third accommodating space 13 can supplement fluid to the inside through the fifth valve 18, and can also achieve communication between the third accommodating space 13 and the external atmosphere, so as to maintain pressure balance between the third accommodating space 13 and the outside, achieve that expansion and contraction of the first elastic cavity 2 are not limited by air pressure, reduce resistance of the atmosphere, and ensure stable operation of the first elastic cavity 2.

Specifically, as shown in fig. 3, in a preferred embodiment, the fifth pipeline 15 and the sixth pipeline 16 respectively adopt a flexible structure, and when the first elastic cavity 2 has a larger volume, a smaller volume or moves, because the fifth pipeline 15 and the sixth pipeline 16 have a margin in the length connecting with the first elastic cavity 2 and are of a flexible structure, the movement of the first elastic cavity 2 is not affected, and in a variation, the fifth pipeline 15 and the sixth pipeline 16 adopt a rigid structure, and the first elastic cavity 2 is connected with the fifth pipeline 15 and the sixth pipeline 15 in a sealing and sliding manner, respectively, so that the present invention can be realized.

Specifically, as shown in fig. 3, in a preferred example, the flow meter system includes a third flow meter and a fourth flow meter, the third flow meter is mounted on the fourth pipeline 14, the fourth flow meter is mounted on the sixth pipeline 16, wherein the third flow meter and the fourth flow meter are respectively electrically connected to the control device 19, and the third flow meter and the fourth flow meter are respectively capable of transmitting the detected flow information of the fluid to the control device 19.

Specifically, as shown in fig. 3, the fifth pipeline 15 is provided with a second check valve, and when the pump body stops rotating, the fluid in the first elastic cavity 2 can be prevented from flowing back into the third accommodating space 13 through the pump body due to the second check valve.

Specifically, in a preferred embodiment, the control device 19 is electrically connected to the fourth valve 17, and the control device 19 can control the fourth valve 17 to open, close or realize the control of the opening size.

The invention also provides a carrier which is installed on the air simple aircraft and comprises a carrier body and a functional load, wherein the carrier body can carry a carrying object, the control device 19 can control the functional load to complete loading and unloading work of the carrying object, in a preferred example, the carrier carries required building materials or tools to a specified place due to building engineering, the functional load adopts a robot, and after the robot detects that the specified place is reached through an intelligent identification system, the robot starts to execute unloading tasks and unloads the carried building materials or tools. In one variation, the vehicle returns the courier to the target location after the functional load detects arrival at the designated location due to the aerial delivery of the courier.

Further, the present invention may also be applied to the performance of various tasks, such as aerial photography, and, for example, the transportation of food clothing by persons trapped in mountains. The invention can also execute high-altitude operation tasks, such as glass cleaning of a high building, and the control device 19 can control functional loads to complete glass cleaning after the aircraft flies to a specified position.

The working principle of the driving mechanism 50 according to the present invention is described separately according to the above two embodiments:

the driving mechanism 50 of the aerial simple aircraft comprises an initial state and a working state, when the system is in the working state, the pressure in the first elastic cavity 2 is between a first pressure threshold and a second pressure threshold, and when the pressure in the first elastic cavity 2 is reduced to the first pressure threshold, the control device controls the pump body to supplement fluid into the first elastic cavity 2; when the pressure inside the first elastic cavity 2 rises to the second pressure threshold, the control device controls the pump body to stop supplying fluid into the first elastic cavity 2, and always keeps the pressure inside the first elastic cavity 2 between the first pressure threshold and the second pressure threshold so as to keep a continuous working state, specifically:

using fig. 6 and 7 asFor example, the driving mechanism 50 operates as follows:

initial state:the initial state can be realized by the control device 19, specifically, the first accommodating space 4 is a sealed negative pressure space, the first elastic cavity 2 is in a hollow state without fluid inside, the control device 19 controls the second valve 11 to open, the fluid enters the second accommodating space 6, the control device 19 receives the flow information of the first flowmeter in real time, when the fluid in the second accommodating space 6 is added to a preset volume, the control device 19 controls the second valve 11 to close, at this time, the motor is started and the pump body is driven to rotate under the control of the control device 19, the fluid in the second accommodating space 6 is driven into the first elastic cavity 2 through the pump body, the fluid in the first elastic cavity 2 gradually changes and expands to drive the sliding member 3 to move close to the second accommodating space 6, and the volume of the first accommodating space 4 gradually increases, the control device 19 receives the flow information of the second flow meter in real time, when the fluid in the first elastic cavity 2 is added to the preset volume, that is, the pressure inside the corresponding first elastic cavity 2 is increased to the second pressure threshold, at this time, the control device 19 controls the motor to stop rotating, and at this time, the setting of the initial state of the device is completed.

The working state is as follows: when the invention works, on one hand, because the first elastic cavity 2 has elasticity, the first elastic cavity 2 which is filled with fluid and is expanded has resilience; on the other hand, since the first accommodation space 4 is a negative pressure chamber, the second accommodation space 6 generates a pressure difference with the first accommodation space 4, and thus the slider 3 tends to move closer to the first accommodation space 4.

Further, during operation, the control device 19 controls the first valve 10 and the second valve 11 to open, on one hand, the first elastic cavity 2 drives the fluid in the first elastic cavity 2 to flow out from the third pipeline 9 under the action of self-resilience force, on the other hand, under the action of atmospheric pressure, the pressure difference generated between the second accommodating space 6 and the first accommodating space 4 drives the sliding member 3 to move close to the first accommodating space 4, so that the sliding member 3 not only presses the first elastic cavity 2 to enable the fluid in the first elastic cavity 2 to flow out rapidly, but also can realize automatic fluid supplement in the second accommodating space 6 under the action of atmospheric pressure, when the residual fluid in the first elastic cavity 2 reaches a preset volume, namely when the pressure corresponding to the interior of the first elastic cavity 2 is reduced to a first pressure threshold value, the control device 19 controls the pump body to rotate again, and the fluid in the second accommodating space 6 is supplemented in the first elastic cavity 2 again through the pump body, until the pressure in the first elastic cavity 2 rises to the second pressure threshold again, the operation is repeated in this way, so that continuous fluid in the first elastic cavity 2 is ensured to flow out through the third pipeline 9, and the requirement of the device is met.

It should be noted that, during the whole operation, the control device 19 can control the opening degree of the first valve 10 according to actual needs, and when the opening degree of the first valve 10 is smaller, the flow rate of the fluid ejected from the third pipeline 9 is fast; when the opening degree of the first valve 10 is large, the flow velocity of the fluid sprayed out of the third pipeline 9 is low, so that the requirements of different energy release strengths are met, controllable thrust is realized, and the actual requirement of flight thrust is met.

Taking fig. 3 as an example, the driving mechanism 50 works as follows:

initial state:the initial state can be controlled by the control device 19, specifically, the third accommodating space 13 is filled with fluid, the first elastic cavity 2 is in a hollow state without fluid inside, the fifth valve 18 is opened, the control device 19 controls the motor to start and drive the pump body to rotate, the fluid in the third accommodating space 13 is pumped into the first elastic cavity 2 through the pump body, when the fluid in the first elastic cavity 2 is added to a preset volume, namely, the pressure inside the first elastic cavity 2 is increased to a second pressure threshold value, the control device 19 controls the motor to stop rotating, and the setting of the initial state of the device is completed.

The working state is as follows: because the first elastic cavity 2 has elasticity, the first elastic cavity 2 filled with fluid and expanded has resilience, so that the elastic force exists for driving the internal fluid to flow out, when the pump works, the control device 19 controls the fourth valve 17 and the fifth valve 18 to be opened, on one hand, the first elastic cavity 2 drives the fluid in the first elastic cavity 2 to flow out from the sixth pipeline 16 under the action of the resilience, on the other hand, the control device 19 controls the opening degree of the fifth valve 18 according to the volume of the first elastic cavity 2 excluding the fluid, and fills the corresponding volume of the fluid into the third accommodating space 13, when the residual fluid in the first elastic cavity 2 reaches the preset volume, namely when the pressure in the corresponding first elastic cavity 2 is reduced to the first pressure threshold value, the control device 19 controls the pump body to rotate again, and the fluid in the third accommodating space 13 is filled into the first elastic cavity 2 again through the pump body, until the pressure in the first elastic cavity 2 rises to the second pressure threshold again, the above steps are repeated to ensure that continuous fluid in the first elastic cavity 2 flows out through the sixth pipeline 16, so as to meet the requirement of the device.

It should be noted that, during the whole operation, the control device 19 can control the opening degree of the fourth valve 17 according to actual needs, and when the opening degree of the fourth valve 17 is small, the flow rate of the fluid flowing out of the sixth pipeline 16 is fast; when the opening degree of the fourth valve 17 is large, the flow rate of the fluid flowing out of the sixth pipeline 16 is slow so as to meet the requirements of different energy release strengths, and the counterforce meets the actual requirement of the flight thrust.

The first pressure threshold and the second pressure threshold in the present invention refer to pressures that ensure the system to work continuously, and the pressure inside the first elastic cavity 2 between the first pressure threshold and the second pressure threshold can ensure that the fluid inside the first elastic cavity 2 flows out continuously and the control of the flow rate is realized by the control of the control device 19.

Further, the first pressure threshold and the second pressure threshold may be monitored by setting a flow meter, and may also be monitored by setting a pressure sensor, when a flow meter is used, how much of the flow output by the control device 19 through the first elastic cavity 2 is output as a control command, when a pressure sensor is used, the control device 19 outputs a control command through the obtained pressure inside the first elastic cavity 2, and when the pressure inside the first elastic cavity 2 is increased due to a change of fluid pressure or decreased due to a change of fluid pressure, the control device 19 executes the control command through information obtained in real time.

The invention provides a low-speed aerial vehicle.A driving mechanism 50 can work under the action of an elastic cavity and the external atmospheric pressure and can also work under the action of the self resilience force of the elastic cavity only based on the fluid air, and the interlocking control is realized by a control device, a pump body and valves, so that the stable and controllable flow rate or flow of fluid is realized, and the low-speed aerial vehicle is noiseless, simple in structure, convenient to operate and wide in application.

The invention can realize the speed-up flying of the aircraft through further improvement, in a preferred embodiment, the fluid in the driving mechanism 50 is set as combustible fluid and stored through a storage device, a plurality of driving mechanisms 50 are respectively connected with the storage device through pipelines, a mixing chamber is arranged on a pipeline through which the combustible fluid flows out in the first elastic cavity 2, the mixing chamber is also connected with a combustion improver pipeline, a combustion improver pipeline control valve is arranged on the combustion improver pipeline, the combustion improver pipeline control valve is electrically connected with the control device 19, the control device 19 can control the opening degree of the combustion improver pipeline control valve, an ignition device is arranged in the mixing chamber, the mixing chamber is arranged at the tail end of the fluid outflow pipeline, when the control device 19 controls the ignition device to ignite, the combustible fluid and the combustion improver are combusted in the mixing chamber to generate airflow expansion and are sprayed out through an outlet of the fluid outflow pipeline, the jet speed is improved, and the flying speed of the aircraft can be accelerated. In a variation, the fluids in the plurality of driving mechanisms 50 are set to be different fluids, for example, the fluid in one part of the driving mechanisms 50 is a combustible agent, the fluid in the other part of the driving mechanisms 50 is a combustion improver, and the ends of the fluid outlet pipes in the two parts of the driving mechanisms 50 respectively enter the corresponding mixing chambers in a one-to-one correspondence manner and are ignited and combusted by the ignition device to realize the injection propulsion force after the fluid expands, thereby achieving the purpose of fast flight.

Furthermore, the adding amount of the combustible fluid stored in the storage device can be added according to the requirement of the flight mission, the flight mission with a set distance can be realized, for example, the aircraft is required to fly for 30 kilometers, and the combustible fluid with a corresponding volume can be added, so that the aircraft can complete the flight mission for 30 kilometers.

Furthermore, the combustible fluid can be a combustible gas, such as hydrogen, or a combustible liquid, such as ethanol, and the combustion improver can be air or oxygen, and is reasonably arranged according to the actual condition of the device; in addition, the fluid outflow pipeline is made of high-temperature-resistant materials with certain strength, can bear the impact of instantaneous combustion expansion force, and does not have chemical reaction with the combustible agent and the combustion improver.

The working principle of the aerial simple aircraft is as follows:

when the aircraft takes off, the control device 19 sends out a guide command to control the gas change generator 31 to generate hydrogen, the generated hydrogen enters the second elastic cavity 32 through the seventh pipeline 33, the second elastic cavity 32 expands, the control device 19 controls the amount of the hydrogen generated by the gas change generator 31 according to the height to be taken off, meanwhile, the branch control valve 36 on the fluid branch pipe 35 which is beneficial to the flight direction is controlled to be opened according to the flight direction of the aircraft, the ejected fluid provides power for the flight of the aircraft to push the aircraft to fly, and the running of the aircraft in the bending direction can also be realized by controlling the on-off of the fluid branch pipes 35 in different directions. During the flight of the aircraft, the plurality of driving mechanisms 50 may operate simultaneously or alternately to meet the actual flight requirements.

The flying height of the height adjusting assembly 30 can be adjusted by adopting a hot air balloon principle, the air in the second elastic cavity 32 can be heated to expand, the flying height of the aircraft can be adjusted, when the air in the second elastic cavity 32 is heated, the expansion buoyancy is increased, or the air is heated to generate a rising trend, the buoyancy of the device is increased, otherwise, the buoyancy of the device is decreased, and the flying height of the device is adjusted, wherein the second elastic cavity 32 is made of a high-temperature-resistant material to meet the requirement of air heating.

When a failure occurs in a certain driving mechanism 50, the control device 19 may determine, according to the received pressure, that there is no change in the pressure at the fluid outlet of the driving mechanism 50 connected to the fluid manifold 34 or that the pressure is abnormal, and the control device 19 may record and stop the operation of the driving mechanism 50, when the landing floor is waited, the worker checks whether there is a damaged driving mechanism 50 through a visual interface on the control device 19, and the worker may timely repair and replace the driving mechanism according to the result of the check.

The invention can also not adopt the fluid main pipe 34, so that the fluid sprayed by the driving mechanism 50 is directly sprayed to the outside of the flight supporting shell 40 to realize the driving force, each driving mechanism 50 works independently and is uniformly controlled by the control device 19, the flight of the whole aircraft can also be realized, the influence on the work of the whole aircraft caused by the fault of the fluid main pipe 34 can also be avoided, and the specific arrangement can be reasonably set according to the actual requirement.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.

Claims

1. An aerial SIMPLE AIRCRAFT, comprising a control device (19), a height adjustment assembly (30), a flight support housing (40) and a drive mechanism (50);

the height adjusting assembly (30) and the driving mechanism (50) are both arranged on the flight supporting shell (40);

the control device (19) is capable of controlling an altitude adjustment assembly (30) to achieve the aircraft altitude adjustment;

the control device (19) can control the driving mechanism (50) to realize the adjustment of the flying direction and provide driving force for flying through the driving mechanism (50).

2. The airborne SIMOX aircraft of claim 1, wherein the drive mechanism (50) comprises an energy storage device housing (1), a first elastic chamber (2), and a fluid transport assembly (5), and comprises any one of the following structural forms:

-further comprising a third conduit (9), the energy storage device housing (1) having a slider (3) arranged therein, the slider (3) dividing the interior of the energy storage device housing (1) into a first accommodation space (4) and a second accommodation space (6), the first elastic cavity (2) being mounted in the first accommodation space (4), the second accommodation space (6) being filled with a fluid; an inlet of the fluid conveying assembly (5) is connected with the second accommodating space (6) through a first pipeline (7), and an outlet of the fluid conveying assembly (5) is connected with the first elastic cavity (2) through a second pipeline (8); when the fluid conveying assembly (5) is started to work, the fluid sequentially passes through the first pipeline (7), the fluid conveying assembly (5) and the second pipeline (8) and enters the first elastic cavity (2) so as to drive the first elastic cavity (2) to enlarge in volume; one end of the third pipeline (9) is connected with the first elastic cavity (2), and the other end of the third pipeline (9) extends to the outside of the energy storage device shell (1);

-a third accommodation space (13) is provided in the energy storage device housing (1), the third accommodation space (13) being filled with a fluid, the first elastic cavity (2) being mounted in the third accommodation space (13); an inlet of the fluid conveying assembly (5) is connected with the third accommodating space (13) through a fourth pipeline (14), and an outlet of the fluid conveying assembly (5) is connected with the first elastic cavity (2) through a fifth pipeline (15); a sixth pipeline (16) is arranged on the first elastic cavity (2), and the sixth pipeline (16) penetrates through the energy storage device shell (1) and extends to the outside of the energy storage device shell (1).

3. The aerial improvised aircraft as claimed in claim 2, characterized in that it comprises any one of the following structural forms:

-a first valve (10) is arranged on the third line (9);

-a fourth valve (17) is arranged on the sixth line (16).

4. The aerial improvised aircraft as claimed in claim 2, characterized in that it comprises any one of the following structural forms:

-further comprising a second valve (11) and a third valve (12), the first containing space (4) being in communication with the outside through the third valve (12), the second containing space (6) being in communication with the outside through the second valve (11); the sliding piece (3) is in sliding sealing fit with the energy storage device shell (1), and a sealing piece is arranged between the sliding piece (3) and the energy storage device shell (1);

-a fifth valve (18) is arranged on the energy storage device housing (1), the third receiving space (13) being in communication with the outside via the fifth valve (18).

5. The airborne SIMOX aircraft of claim 2, wherein said fluid transfer assembly (5) comprises any one of the following structures:

-comprising a pump body and an electric motor capable of driving the pump body in rotation, the control device (19) being electrically connected to the electric motor, the control device (19) being electrically connected to the first valve (10) or the fourth valve (17);

-comprising a linkage rod (22), a fluid actuator (38) and a power actuator (39), wherein the linkage rod (22) is provided with a first connecting end (23) and a second connecting end (24), the first connecting end (23) extends into the fluid actuator (38) and forms a fourth accommodating space (25) with the fluid actuator (38), the second connecting end (24) extends into the power actuator (39) and forms a fifth accommodating space (26) with the power actuator (39), a first driving body (27) is arranged in the fifth accommodating space (26), the linkage rod (22) can move between a first position and a second position, the space of the fourth accommodating space (25) is the smallest in the first position, and the space of the fourth accommodating space (25) is the largest in the second position; the linkage rod (22) can move from a first position to a second position under the driving of the first driving body (27); the linkage rod (22) can move from the second position to the first position under the driving of the first driving body (27) and/or the external atmospheric pressure;

-comprising a drive carrier (41), a fixing bar (42), a fluid carrier (43) and a second drive body (46), one end of the drive carrier (41) extending into the interior of the fluid carrier (43) and forming a sixth receiving space (44) with the fluid carrier (43), the other end of the drive carrier (41) being a free end, the fixing bar (42) being mounted inside the drive carrier (41) and forming a seventh receiving space (45) with the drive carrier (41), the second drive body (46) being mounted in the seventh receiving space (45), the drive carrier (41) being movable between a third position, in which the space of the sixth receiving space (44) is minimal, and a fourth position, in which the space of the sixth receiving space (44) is maximal; the driving carrier (41) can move from the fourth position to the third position under the driving of the second driving body (46); the drive carrier (41) is movable from the third position to the fourth position under the urging of the second drive body (46) and/or the external atmospheric pressure;

-comprising a third driving body (47), an annular casing (48), a bulkhead (49) and a pushing assembly (51), said bulkhead (49) and said pushing assembly (51) being mounted inside the annular casing (48) and dividing the inside of the annular casing (48) into an eighth housing space (52) and a ninth housing space (53), said third driving body (47) being mounted in the eighth housing space (52), said pushing assembly (51) being movable between a fifth position, in which the space of the ninth housing space (53) is maximum, and a sixth position, in which the space of the ninth housing space (53) is minimum; the push assembly (51) can move from the fifth position to the sixth position under the urging of the third drive body (47); the push assembly (51) can move from the sixth position to the fifth position under the urging of the third driving body (47) and/or the external atmospheric pressure.

6. The airborne SIMPLE COMBUSTION AIRCRAFT according to claim 2, characterized in that the second conduit (8) comprises any of the following connection forms:

the second pipeline (8) is connected with the first elastic cavity (2) through the energy storage device shell (1) and the sliding part (3) in sequence; the second pipeline (8) moves along with the sliding piece (3) when the sliding piece (3) slides;

-the second line (8) is connected to the first elastic chamber (2) in turn via the energy storage device housing (1).

7. The airborne SIMOX aircraft of claim 2, characterized in that one or more first pressure sensors (20) are arranged inside the energy storage device housing (1), the first pressure sensors (20) being electrically connected to the control device (19); and/or

A second pressure sensor (21) is arranged on the outer surface or inside the first elastic cavity (2), and the second pressure sensor (21) is electrically connected with the control device (19);

wherein the first pressure sensor (20) and/or the second pressure sensor (21) adopt force variation type sensors or strain type sensors.

8. The airborne SIMOX aircraft of claim 1, wherein the height adjustment assembly (30) comprises a gas change generator (31), a second flexible chamber (32) and a seventh conduit (33);

the gas change generator (31) is connected with the second elastic cavity (32) through a seventh pipeline (33);

the control device (19) is capable of controlling the gas change generator (31) to generate gas according to the aircraft demand and to feed the gas into the second elastic chamber (32) through a seventh conduit (33).

9. The airborne SIMOX hybrid vehicle of claim 2, further comprising a fluid manifold (34), wherein the number of the driving mechanisms (50) is multiple, and the third pipeline (9) or the sixth pipeline (16) on the driving mechanisms (50) is connected with the fluid manifold (34);

the fluid main pipe (34) extends to form a plurality of fluid branch pipes (35), and the plurality of fluid branch pipes (35) are connected with the flight support shell (40) and can spray fluid in the fluid main pipe (34) to the outside of the flight support shell (40) so as to provide power for the flight of the flight support shell (40).

10. A vehicle mounted on the simple aerial vehicle of any one of claims 1 to 9, comprising a carrier capable of carrying a payload, and a functional load;

the control device (19) can control the functional load action to finish loading and unloading of the carried object.