CN216709667U - Unmanned aerial vehicle laying device and navigation equipment - Google Patents

Abstract

The application provides device and navigation equipment are put to unmanned aerial vehicle cloth, include: the launching tube is internally provided with a launching cavity for accommodating the unmanned aerial vehicle, the top of the launching tube is provided with a launching port communicated with the launching cavity, and the bottom of the launching tube is provided with a first air inlet; the pushing device comprises a first piston and an elastic piece, the first piston is movably mounted at the bottom of the launching tube, a first air pressure cavity is formed between the first piston and the inner wall of the bottom of the launching tube, the first piston can move along the length direction of the launching tube, the elastic piece is located on one side, away from the bottom of the launching tube, of the first piston, one end of the elastic piece is abutted to the first piston, and the other end of the elastic piece is abutted to the unmanned aerial vehicle; the gas supply device can input gas with preset gas pressure into the first gas pressure cavity to enable the first piston to move towards the emission opening after being pressed; by adopting the technical scheme: reduce gaseous atmospheric pressure too big and cause first piston to form unsuitable thrust, and then damage unmanned aerial vehicle, reduce the risk of unmanned aerial vehicle damage.

Description

Unmanned aerial vehicle laying device and navigation equipment

Technical Field

The application relates to the technical field of navigation equipment, more specifically say so, relate to an unmanned aerial vehicle lays device and navigation equipment.

Background

The unmanned aerial vehicle has the advantages of strong maneuverability, flexible visual field and the like, and can realize work tasks such as target identification, positioning, tracking and the like on the sea. But the present time of endurance of unmanned aerial vehicle is shorter, in some marine task demands that need deploy unmanned aerial vehicle for a long time, hardly full play unmanned aerial vehicle's advantage, unmanned aerial vehicle carries on and lays the transmission on can submerging unmanned ship in the trade at present, in addition, unmanned aerial vehicle is putting the in-process because the impact force of laying the device and giving is great, causes the impaired problem of unmanned aerial vehicle easily.

Content of application

An object of this application is to provide an unmanned aerial vehicle lays device and navigation equipment to the unmanned aerial vehicle that exists lays device causes the impaired technical problem of unmanned aerial vehicle easily among the solution prior art.

For realizing above-mentioned purpose, the technical scheme that this application adopted is device is put to unmanned aerial vehicle, includes:

the launching tube is internally provided with a launching cavity for accommodating the unmanned aerial vehicle, the top of the launching tube is provided with a launching port communicated with the launching cavity, and the bottom of the launching tube is provided with a first air inlet;

the pushing device comprises a first piston and an elastic piece, the first piston is movably mounted at the bottom of the launching tube, a first air pressure cavity is formed between the first piston and the inner wall of the bottom of the launching tube, the first piston can move along the length direction of the launching tube, the elastic piece is located on one side, away from the bottom of the launching tube, of the first piston, one end of the elastic piece is abutted to the first piston, and the other end of the elastic piece is abutted to the unmanned aerial vehicle;

and the gas supply device is communicated with the first gas inlet and can input gas with preset gas pressure into the first gas pressure cavity, so that the first piston moves towards the emission opening after being pressed.

By adopting the technical scheme:

firstly, the gas supply device provides gas with preset gas pressure to push the first piston in the first gas pressure cavity, so that the gas pressure of the gas can be adjusted according to the unmanned aerial vehicle to be launched, and improper thrust of the first piston caused by overlarge gas pressure is reduced, and the unmanned aerial vehicle is further damaged;

secondly, the air pressure generated by the air supplied by the air supply device is converted into the elastic force of the elastic piece through the first piston, so that the acting force on the unmanned aerial vehicle is gradually weakened, and the risk of damage to the unmanned aerial vehicle is reduced;

finally, the elastic component is arranged between unmanned aerial vehicle and the first piston, has the function of buffering effort, further reduces the risk that unmanned aerial vehicle damaged.

In one embodiment, the inner wall of the launching tube is provided with a limiting structure which is spaced from the bottom of the launching tube by a preset distance, and the limiting structure is positioned on one side of the first piston, which is far away from the bottom of the launching tube, so that the first piston moves within a preset distance range.

Through adopting above-mentioned technical scheme, limit structure restricts the removal stroke of first piston for first piston can only remove in predetermineeing the distance within range, avoids first piston removal stroke too big and causes too big to unmanned aerial vehicle's thrust, and then leads to unmanned aerial vehicle impaired.

In one embodiment, the launching barrel comprises a first barrel and a second barrel connected with the first barrel, a ventilation channel is arranged between the first barrel and the second barrel in a communication mode, the limiting structure is arranged between the first barrel and the second barrel, and when the first piston abuts against the limiting structure, the first air pressure cavity is communicated with the launching cavity.

Through adopting above-mentioned technical scheme, the passageway of ventilating communicates first atmospheric pressure chamber and transmission chamber, and when first piston supported in limit structure, the gas in first atmospheric pressure chamber can reveal to the transmission chamber in through the passageway of ventilating, and then discharges from the transmission chamber, reduces the gas pressure in first atmospheric pressure chamber, and then reduces the effort of applying at first piston to reduce the effort of applying on unmanned aerial vehicle, reduced the impaired risk of unmanned aerial vehicle.

In one embodiment, thrust unit still includes to be located the second piston in the second barrel, a side of second piston is used for bearing unmanned aerial vehicle, another side of second piston with the elastic component deviate from the one end butt of first piston, the second piston, first piston with the inner wall of launching tube forms second pneumatic chamber, first piston with during limit structure butt, first pneumatic chamber with second pneumatic chamber intercommunication.

Through adopting above-mentioned technical scheme, the passageway of ventilating communicates first atmospheric pressure chamber and second atmospheric pressure chamber for the atmospheric pressure in first atmospheric pressure chamber and the atmospheric pressure in second atmospheric pressure chamber reduce gradually, and then make the effort of applying on unmanned aerial vehicle reduce gradually, reduce the impaired risk of unmanned aerial vehicle.

In one embodiment, the first cylinder has an inner diameter smaller than an inner diameter of the second cylinder, the first piston has an outer diameter matching the inner diameter of the first cylinder, and the second piston has an outer diameter matching the inner diameter of the second cylinder.

Through adopting above-mentioned technical scheme, first barrel and second barrel simple structure easily form limit structure, do benefit to processing.

In one embodiment, the launch canister further comprises a cover body sealing the launch opening, the cover body being detachably connected with the launch canister.

Through adopting above-mentioned technical scheme, the lid can be dismantled with the launching tube and be connected, and unmanned aerial vehicle can be followed the launching cavity and broken away the lid and launched outwards, has guaranteed promptly that unmanned aerial vehicle cloth puts the device and can use under water, and unmanned aerial vehicle's that the while is also guaranteed cloth is put.

In one embodiment, the launching tube is further provided with a second air inlet communicated with the launching cavity, the second air inlet is communicated with the air supply device, and the air supply device can input air with preset air pressure into the launching cavity to enable the cover body to be separated from the launching port.

Through adopting above-mentioned technical scheme, when having guaranteed the launching tube leakproofness that unmanned aerial vehicle laid the device, realize the automation of lid and open.

In one embodiment, the cover body and the launching tube are flexibly connected through a rope.

Through adopting above-mentioned technical scheme, lid and launching tube pass through line body flexonics, prevent effectively that lid, unmanned aerial vehicle and launching tube from being damaged by the lid that drops.

In one embodiment, the gas supply device comprises a high-pressure gas supply assembly, a pressure reducing assembly, a flow dividing assembly, a control assembly, a first gas pipeline and a second gas pipeline which are sequentially connected, wherein the first gas pipeline is used for being communicated with the first air pressure cavity, and the second gas pipeline is used for being communicated with the emission cavity.

Through adopting above-mentioned technical scheme, improved the degree of automation that device was put to unmanned aerial vehicle cloth.

This embodiment still provides a navigation equipment, including navigation main part and foretell unmanned aerial vehicle layout device, launching tube perpendicular or slope set up in on the navigation main part.

Through adopting above-mentioned technical scheme, the navigation equipment of this embodiment sets up multistage accuse pressure equipment, greatly reduced in the damage rate that unmanned aerial vehicle was laid to the equipment of navigating, unmanned aerial vehicle lay the device can realize slope or arrange perpendicularly on the equipment of navigating, increase the flexibility ratio of arranging, and the mode maximum degree of laying perpendicularly reduces the space that unmanned aerial vehicle laid the device and occupied the equipment of navigating.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle deployment device provided in an embodiment of the present application;

fig. 2 is a schematic diagram of a first air pressure chamber of an unmanned aerial vehicle deployment device provided in an embodiment of the present application before inflation;

fig. 3 is a schematic diagram of a first air pressure chamber of an unmanned aerial vehicle deployment device according to an embodiment of the present application after being inflated;

fig. 4 is a schematic view of an elastic member of an unmanned aerial vehicle deployment device provided in an embodiment of the present application in a compressed state;

fig. 5 is a schematic diagram of a second pneumatic chamber of the unmanned aerial vehicle deployment device provided in the embodiment of the present application after being inflated;

FIG. 6 is an enlarged view at "A" of FIG. 5;

fig. 7 is a schematic structural diagram of a navigation device provided in an embodiment of the present application.

The figures are numbered:

100-unmanned aerial vehicle laying device;

1-a launch canister; 2-a pushing device; 3-a gas supply device; 4-unmanned aerial vehicle;

10-a launch chamber; 20-a first pneumatic chamber; 30-a second pneumatic chamber;

11-an emission port; 12-a first air inlet; 13-a limit structure; 14-a first cylinder; 15-a second cylinder; 16-a vent channel; 17-a cover body; 18-a second air inlet; 21-a first piston; 22-an elastic member; 23-a second piston; 31-a high pressure gas supply assembly; 32-a pressure relief assembly; 33-a flow splitting assembly; 34-a control assembly; 35-a first gas conduit; 36-second gas conduit.

Detailed Description

In order to make the technical problems, technical solutions and advantageous effects to be solved by the present application clearer, the present application is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.

It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected or indirectly connected to the other element.

It will be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, refer to an orientation or positional relationship illustrated in the drawings for convenience in describing the present application, and do not indicate that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and are thus not to be construed as limiting the present application.

Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating relative importance or as indicating a number of technical features. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise. Specific implementations of the present application are described in more detail below with reference to specific embodiments:

as shown in fig. 1 and fig. 2, an unmanned aerial vehicle deployment device 100 provided in an embodiment of the present application includes: the device comprises a launching tube 1, a pushing device 2 and an air supply device 3; the launching tube 1 is internally provided with a launching cavity 10 for accommodating the unmanned aerial vehicle, the top of the launching tube 1 is provided with a launching port 11 communicated with the launching cavity 10, and the bottom of the launching tube 1 is provided with a first air inlet 12; the pushing device 2 comprises a first piston 21 and an elastic part 22, the first piston 21 is movably installed at the bottom of the launching tube 1, a first air pressure cavity 20 is formed in the inner wall of the bottom of the first piston 21 and the bottom of the launching tube 1, the first piston 21 can move along the length direction of the launching tube 1, the elastic part 22 is located on one side, departing from the bottom of the launching tube 1, of the first piston 21, one end of the elastic part 22 is abutted to the first piston 21, and the other end of the elastic part 22 is abutted to the unmanned aerial vehicle 4; the gas supply device 3 is communicated with the first gas inlet 12, and the gas supply device 3 can input gas with preset gas pressure into the first gas pressure cavity 20, so that the first piston 21 moves towards the emission opening 11 after being pressed.

Referring to fig. 3 to fig. 5, the working principle of the unmanned aerial vehicle deployment device 100 provided in this embodiment is as follows:

place unmanned aerial vehicle 4 in launching chamber 10, and with elastic component 22's other end butt, first piston 21 is close to the bottom surface of launching tube 1, gas supply unit 3 will predetermine the gaseous first air pressure chamber 20 of 12 inputs of air inlet, gaseous atmospheric pressure promotes first piston 21 and removes towards launching port 11, elastic component 22 receives the pressure emergence compression of first piston 21, gaseous effort to first piston 21 converts the elasticity potential energy of elastic component 22 into promptly, kick-back after the elastic component 22 compression, apply elasticity on unmanned aerial vehicle 4, order about unmanned aerial vehicle 4 and remove towards launching port 11, jet out from launching port 11 until unmanned aerial vehicle 4, accomplish unmanned aerial vehicle 4 transmission action.

By adopting the technical scheme:

firstly, the gas supply device 3 provides gas with preset gas pressure to push the first piston 21 in the first gas pressure cavity 20, so that the gas pressure of the gas can be adjusted according to the unmanned aerial vehicle 4 to be launched, and improper thrust formed by the first piston 21 due to overlarge gas pressure is reduced, and the unmanned aerial vehicle 4 is further damaged;

secondly, the air pressure generated by the air supplied by the air supply device 3 is converted into the elastic force of the elastic part 22 through the first piston 21, so that the acting force on the unmanned aerial vehicle 4 is gradually weakened, and the risk of damage to the unmanned aerial vehicle 4 is reduced;

finally, the elastic element 22 is interposed between the drone 4 and the first piston 21, having the function of buffering the forces, further reducing the risk of damage to the drone 4.

As shown in fig. 5 and 6, in one embodiment, the inner wall of the launch barrel 1 is provided with a limit structure 13 spaced from the bottom of the launch barrel 1 by a preset distance, and the limit structure 13 is located on a side of the first piston 21 away from the bottom of the launch barrel 1, so that the first piston 21 moves within a preset distance range.

Specifically, the limiting structure 13 is convexly arranged on the inner wall of the launching tube 1, and the limiting structure 13 can be penetrated by the elastic element 22 to just limit the movement of the first piston 21; launch unmanned aerial vehicle 4 before, first piston 21 is located the position that is close to the bottom surface of launching tube 1, in the first atmospheric pressure chamber 20 of gaseous input that air feeder 3 will predetermine atmospheric pressure, promote first piston 21 and remove towards launching port 11, first piston 21 compression elastic component 22, first piston 21 continues to remove towards launching port 11 this moment, support on limit structure 13 until first piston 21, first piston 21 stops to remove, elastic component 22 begins to kick-back, apply elasticity on unmanned aerial vehicle 4, order about unmanned aerial vehicle 4 to remove towards the transmission.

Through adopting above-mentioned technical scheme, limit structure 13 restricts first piston 21's removal stroke for first piston 21 can only remove in predetermineeing the distance within range, avoids first piston 21 to remove the stroke too big and cause too big to unmanned aerial vehicle 4's thrust, and then leads to unmanned aerial vehicle 4 impaired.

In one embodiment, the launching tube 1 comprises a first tube body 14 and a second tube body 15 connected with the first tube body 14, a ventilation channel 16 is arranged between the first tube body 14 and the second tube body 15 in a communication mode, a limiting structure 13 is arranged between the first tube body 14 and the second tube body 15, and when the first piston 21 abuts against the limiting structure 13, the first air pressure cavity 20 is communicated with the launching cavity 10.

Specifically, the gas supply device 3 inputs gas with a preset gas pressure into the first gas pressure cavity 20, and pushes the first piston 21 to move towards the emission opening 11 until the first piston 21 abuts against the limiting structure 13, and at this time, the first gas pressure cavity 20 is communicated with the emission cavity 10 through the vent channel 16, so that the gas in the first gas pressure cavity 20 can be leaked into the emission cavity 10 through the vent channel 16.

Through adopting above-mentioned technical scheme, vent passage 16 communicates first atmospheric pressure chamber 20 and transmission chamber 10, when first piston 21 supports in limit structure 13, the gas in first atmospheric pressure chamber 20 can reveal to transmission chamber 10 in through vent passage 16, and then discharge from transmission chamber 10, reduce the gas pressure in first atmospheric pressure chamber 20, and then reduce the effort of applying at first piston 21, thereby reduced the effort of applying on unmanned aerial vehicle 4, reduce the impaired risk of unmanned aerial vehicle 4.

In one embodiment, the pushing device 2 further includes a second piston 23 located in the second cylinder 15, one side surface of the second piston 23 is used for bearing the unmanned aerial vehicle 4, the other side surface of the second piston 23 is abutted with one end of the elastic member 22, which is away from the first piston 21, the second piston 23, the first piston 21 and the inner wall of the launch barrel 1 form a second air pressure cavity 30, and when the first piston 21 is abutted with the limiting structure 13, the first air pressure cavity 20 is communicated with the second air pressure cavity 30.

Specifically, the gas supply device 3 inputs gas with a preset gas pressure into the first gas pressure cavity 20, and pushes the first piston 21 to move toward the emission port 11 until the first piston 21 abuts against the limiting structure 13, at this time, the first gas pressure cavity 20 is communicated with the second gas pressure cavity 30 through the ventilation channel 16, so that the gas in the first gas pressure cavity 20 can be transmitted to the second gas pressure cavity 30 through the ventilation channel 16, although the gas pressure in the second gas pressure cavity 30 and the gas pressure in the first gas pressure cavity 20 decrease, the gas pressure in the second gas pressure cavity 30 can still push the second piston 23 together with the elastic member 22, so as to provide power to the second piston 23, and further drive the unmanned aerial vehicle 4 to emit.

Through adopting above-mentioned technical scheme, the passageway 16 that ventilates communicates first atmospheric pressure chamber 20 and second atmospheric pressure chamber 30 for the atmospheric pressure of first atmospheric pressure chamber 20 and the atmospheric pressure of second atmospheric pressure chamber 30 reduce gradually, and then make the effort of applying on unmanned aerial vehicle 4 reduce gradually, reduce the impaired risk of unmanned aerial vehicle 4.

In one embodiment, the inner diameter of the first cylinder 14 is smaller than the inner diameter of the second cylinder 15, the outer diameter of the first piston 21 matches the inner diameter of the first cylinder 14, and the outer diameter of the second piston 23 matches the inner diameter of the second cylinder 15.

Specifically, a stepped limiting structure 13 is formed between the first cylinder 14 and the second cylinder 15, so that the first piston 21 can be limited by the stepped limiting structure 13, and the limiting structure 13 is enabled to avoid the elastic member 22.

Through adopting above-mentioned technical scheme, first barrel 14 and second barrel 15 simple structure easily form limit structure 13, do benefit to processing.

In one embodiment, the launch barrel 1 further comprises a cover 17 sealing the launch opening 11, the cover 17 being removably attached to the launch barrel 1.

Specifically, the lid 17 is used for sealing this launch canister 1 for unmanned aerial vehicle laying device 100 can use under water, makes it can be applicable to on the unmanned submersible ship.

Through adopting above-mentioned technical scheme, lid 17 can dismantle with launch canister 1 and be connected, and unmanned aerial vehicle 4 can be followed launch chamber 10 and broken away lid 17 and outwards launched, has guaranteed promptly that unmanned aerial vehicle laying device 100 can use under water, and the unmanned aerial vehicle 4's that also guarantee simultaneously is laid.

In one embodiment, the launch barrel 1 is further provided with a second gas inlet 18 communicating with the launch chamber 10, the second gas inlet 18 communicating with the gas supply device 3, the gas supply device 3 being capable of inputting gas of a predetermined pressure into the launch chamber 10 to disengage the cover 17 from the launch opening 11.

Specifically, the gas supply device 3 may be used to input gas into the launching chamber 10 when deploying the drone 4, opening the cover 17 by gas pressure.

Through adopting above-mentioned technical scheme, when having guaranteed that unmanned aerial vehicle lays the launch canister 1 leakproofness of device 100, realize the automation of lid 17 and open.

In one embodiment, the cover 17 and the launch barrel 1 are flexibly connected by a cord.

Through adopting above-mentioned technical scheme, lid 17 passes through line body flexonics with launch canister 1, prevents effectively that lid 17, unmanned aerial vehicle 4 and launch canister 1 from being damaged by the lid 17 that drops.

Referring to fig. 1 again, in one embodiment, the gas supply device 3 includes a high pressure gas supply assembly 31, a pressure reducing assembly 32, a flow dividing assembly 33, a control assembly 34, a first gas pipeline 35 and a second gas pipeline 36 which are connected in sequence, wherein the first gas pipeline 35 is used for communicating with the first pressure chamber 20, and the second gas pipeline 36 is used for communicating with the launching chamber 10.

Specifically, the pressure reducing assembly 32 comprises a ball valve, a multistage pressure reducer, a three-way joint and a safety valve assembly, and the flow dividing assembly 33 comprises an electromagnetic valve and a remote control cabinet; the high-pressure gas supply assembly 31, the pressure reducing assembly 32, the flow dividing assembly 33 and the control assembly 34 are communicated through pipelines.

The ball valve is arranged at the joint of the tail end of the high-pressure gas supply assembly 31 and the pressure reducing assembly 32, the on-off of the high-pressure gas supply assembly 31 is convenient to control (if the pressure reducing assembly 32 breaks down), a multistage pressure reducer is arranged in the pressure reducing assembly 32, at least 1 stage of pressure reducer device can be arranged, the ball valve is arranged at the tail end of the pressure reducing assembly 32, for the safety of the whole high-pressure gas system, the safety valve assembly is arranged at the tail end of the ball valve and comprises a three-way joint and a safety valve, and gas reduced in pressure by the pressure reducing assembly 32 is medium-pressure gas.

The flow dividing assembly 33 can be selected as a control solenoid valve set and is connected by two air outlet pipelines, wherein a first air pipeline 35 is connected with the first air inlet 12 for pushing the movement of the pushing device 2, and a second air pipeline 36 is connected with the second air inlet 18 for automatically opening the cover 17 by air when the cover is laid. Receiving an external instruction in the remote control case, controlling the closing state of the first gas pipeline 35 and the second gas pipeline 36, if the unmanned aerial vehicle 4 needs to be arranged, firstly introducing gas into the second gas pipeline 36 to the launching cavity 10, and opening the cover body 17; then let in first pipeline gas and aerify first atmospheric pressure chamber 20, perhaps first gas pipeline 35 and second gas pipeline 36 ventilate simultaneously, realize opening lid 17 and launch unmanned aerial vehicle 4 synchronous.

Through adopting above-mentioned technical scheme, improved the degree of automation that device 100 was put to unmanned aerial vehicle cloth.

As shown in fig. 7, the present embodiment further provides a navigation device, which includes a navigation body and the above-mentioned unmanned aerial vehicle deployment device 100, wherein the launching tube 1 is vertically or obliquely disposed on the navigation body.

Through adopting above-mentioned technical scheme, the navigation equipment of this embodiment sets up multistage accuse pressure equipment, greatly reduced in the damage rate that unmanned aerial vehicle 4 was laid to the equipment of navigating, unmanned aerial vehicle laying device 100 can realize slope or arrange perpendicularly on the equipment of navigating, increases the flexibility ratio of arranging, and the mode maximum degree of putting perpendicularly reduces the space that unmanned aerial vehicle laying device 100 occupied the equipment of navigating.

The embodiment also provides an unmanned aerial vehicle deployment method, which is applied to the navigation equipment and comprises the following steps:

s1, the medium pressure gas performs work for the first time: after the high-pressure gas output by the high-pressure gas supply assembly 31 is processed by the pressure reducing assembly 32, medium-pressure gas is formed, and the medium-pressure gas enters the first air pressure cavity 20 of the launching tube 1 through the first gas inlet 12 to push the first machine member 21;

s2, the elastic member 22 compresses and decompresses: after the first machine member 21 is pushed by the medium-pressure gas, the elastic member 22 is compressed, at this time, the elastic member 22 absorbs part of the force of the pushing force, and at this time, the elastic member 22 moves to the position of the limiting structure 13, and the elastic member 22 is still in a compressed state;

s3, the elastic member 22 performs the second work: the first part 21 is located limit structure 13, and elastic component 22 produces elasticity, and unmanned aerial vehicle 4 receives the thrust of elastic component 22, and unmanned aerial vehicle 4 launches from launching tube 1.

In one embodiment, step S3 is specifically:

s3, the elastic member 22 does the second work: the first machine member 21 is located at the position limiting structure 13, the elastic member 22 generates elastic force, the second machine member 23 receives the thrust of the elastic member 22, and the second machine member 23 pushes the unmanned aerial vehicle 4 out of the launcher 1.

In one embodiment, step S3 is specifically:

s3, the elastic member 22 does the second work: the first machine member 21 is located at the position of the limiting structure 13, the elastic member 22 generates elastic force, the second machine member 23 is pushed by the thrust of the elastic member 22 to push the unmanned aerial vehicle 4, and the medium-pressure gas in the first air pressure chamber 20 enters the second air pressure chamber 30 through the ventilation channel 16 to form low-pressure gas to push the unmanned aerial vehicle 4.

Through adopting above-mentioned technical scheme, the pressure through above-mentioned each stage is alleviated, finally effectively releases unmanned aerial vehicle.

The above description is only exemplary of the present application and should not be taken as limiting the present application, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims (10)

1. An unmanned aerial vehicle deployment device (100), comprising:

the unmanned aerial vehicle launching device comprises a launching tube (1), wherein a launching cavity (10) for accommodating an unmanned aerial vehicle (4) is formed in the launching tube (1), a launching port (11) communicated with the launching cavity (10) is formed in the top of the launching tube (1), and a first air inlet (12) is formed in the bottom of the launching tube (1);

the pushing device (2) comprises a first piston (21) and an elastic piece (22), the first piston (21) is movably mounted at the bottom of the launching tube (1), a first air pressure cavity (20) is formed in the inner wall of the bottom of the launching tube (1) and the first piston (21), the first piston (21) can move in the length direction of the launching tube (1), the elastic piece (22) is located on one side, deviating from the bottom of the launching tube (1), of the first piston (21), one end of the elastic piece (22) is abutted to the first piston (21), and the other end of the elastic piece (22) is abutted to the unmanned aerial vehicle (4);

air feeder (3), with first air inlet (12) intercommunication, air feeder (3) can be with the gaseous input of predetermineeing atmospheric pressure in first atmospheric pressure chamber (20), make behind first piston (21) the pressurized court emission mouth (11) remove.

2. The unmanned aerial vehicle deployment device (100) of claim 1, wherein the inner wall of the launch barrel (1) is provided with a limit structure (13) which is spaced from the bottom of the launch barrel (1) by a preset distance, and the limit structure (13) is located on one side of the first piston (21) which is far away from the bottom of the launch barrel (1), so that the first piston (21) moves within a preset distance range.

3. The unmanned aerial vehicle laying device (100) of claim 2, wherein the launch canister (1) comprises a first canister body (14) and a second canister body (15) connected with the first canister body (14), a ventilation channel (16) is arranged between the first canister body (14) and the second canister body (15) in a communication mode, the limit structure (13) is arranged between the first canister body (14) and the second canister body (15), and when the first piston (21) abuts against the limit structure (13), the first air pressure cavity (20) is communicated with the launch cavity (10).

4. The unmanned aerial vehicle laying device (100) of claim 3, wherein the pushing device (2) further comprises a second piston (23) located in the second cylinder (15), one side of the second piston (23) is used for bearing the unmanned aerial vehicle (4), the other side of the second piston (23) abuts against one end, away from the first piston (21), of the elastic member (22), the second piston (23), the first piston (21) and the inner wall of the launching tube (1) form a second air pressure cavity (30), and when the first piston (21) abuts against the limiting structure (13), the first air pressure cavity (20) is communicated with the second air pressure cavity (30).

5. The drone disposing device (100) of claim 4, wherein the first cylinder (14) has an inner diameter smaller than the inner diameter of the second cylinder (15), the first piston (21) has an outer diameter matching the inner diameter of the first cylinder (14), and the second piston (23) has an outer diameter matching the inner diameter of the second cylinder (15).

6. The unmanned aerial vehicle deployment device (100) of claim 1, wherein the launch canister (1) further comprises a cover (17) sealing the launch opening (11), the cover (17) being detachably connected to the launch canister (1).

7. The unmanned aerial vehicle laying device (100) of claim 6, wherein the launch canister (1) is further provided with a second air inlet (18) communicated with the launch chamber (10), the second air inlet (18) is communicated with the air supply device (3), and the air supply device (3) can input air with preset air pressure into the launch chamber (10) to enable the cover body (17) to be separated from the launch opening (11).

8. The drone laying device (100) according to claim 6 or 7, characterised in that the cover (17) and the launch canister (1) are flexibly connected by a rope.

9. The unmanned aerial vehicle deployment device (100) of any one of claims 1 to 7, wherein the gas supply device (3) comprises a high-pressure gas supply assembly (31), a pressure reduction assembly (32), a flow dividing assembly (33), a control assembly (34), a first gas pipeline (35) and a second gas pipeline (36) which are connected in sequence, the first gas pipeline (35) is used for communicating with the first air pressure chamber (20), and the second gas pipeline (36) is used for communicating with the launching chamber (10).

10. A navigation device, characterized by comprising a navigation body and the drone deployment apparatus (100) of any one of claims 1 to 9, the launch canister (1) being vertically or obliquely arranged on the navigation body.

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