CN111977011B - Launch device for multi-rotor aircraft and control method thereof - Google Patents

Abstract

The invention discloses a throwing device for a multi-rotor aircraft and a control method thereof, wherein the throwing device comprises a connecting seat and a control device, the connecting seat is provided with more than one guide rail, the guide rails are distributed in an annular array and are provided with a launching bin matched with the multi-rotor unmanned aerial vehicle, the guide rail is provided with a self-driven sliding block assembly for conveying the multi-rotor unmanned aerial vehicle to the top end of the launching bin, the self-driven sliding block assembly is provided with a dovetail tenon, the guide rail is provided with a vertical guide groove matched with the dovetail tenon, the front surfaces of the self-driven sliding block assemblies are respectively provided with a catapulting device for popping the multi-rotor unmanned aerial vehicle, and the catapulting device is provided with an adsorption mechanism for adsorbing the multi-rotor unmanned aerial vehicle in conveying; this a put in device for many rotor crafts can put in a plurality of unmanned aerial vehicle in proper order, in the occasion that needs many rotor unmanned aerial vehicle, can reduce the demand to the place of taking off, reduces the time of putting.

Description

Launch device for multi-rotor aircraft and control method thereof

Technical field

The invention relates to a delivery device for a multi-rotor aircraft and a control method thereof.

Background technique

A multi-rotor UAV is a special unmanned helicopter with three or more rotor axes. It rotates through electric motors on each axis to drive the rotors, thereby generating lift and thrust. The collective pitch of the rotors is fixed, unlike that of a regular helicopter, which is variable. By changing the relative speed between different rotors, the magnitude of the single-axis propulsion can be changed, thereby controlling the trajectory of the aircraft. It has strong controllability and can take off and land vertically and hover. It is mainly suitable for low-altitude, low-speed missions with vertical take-off, landing and hovering requirements.

At present, when multiple multi-rotor drones work together, it is often necessary to place the drones, resulting in a greater demand for space. Therefore, it is necessary to provide a launch device for multi-rotor aircraft to reduce the need for take-off. The needs of the venue reduce the placement time.

Contents of the invention

The technical problem to be solved by the present invention is to provide a launching device for multi-rotor aircraft, which can launch multiple drones in sequence. When multiple multi-rotor drones are needed, it can reduce the impact on the take-off location. needs to reduce display time.

In order to solve the above problems, the present invention adopts the following technical solutions:

A delivery device for a multi-rotor aircraft, including a connecting seat and a control device. The connecting seat is provided with a guide rail, and there are more than one guide rails. The guide rails are distributed in an annular array and formed with a multi-rotor unmanned aerial vehicle. The launch bay is paired with the camera. The guide rail is fixedly connected to the connecting base. The guide rail is provided with a self-driven slider assembly for transporting the multi-rotor UAV to the top of the launch bay. The self-driven slider component is provided with There is a dovetail tenon, the guide rail is provided with a vertical guide groove that matches the dovetail tenon, the self-driven slider assembly and the guide rail are slidingly connected through the vertical guide groove, and the self-driven slider assembly is provided with more than one, The front of the self-driven slider assembly is equipped with an ejection device for ejecting the multi-rotor UAV. The ejection device is located in the launch chamber. The ejection device is provided with an ejection device for adsorbing the multi-rotor UAV during transportation. Adsorption mechanism, the self-driven slider assembly, the ejection device and the adsorption mechanism are all electrically connected to the control device.

Preferably, a first connecting ring and a second connecting ring are provided above the connecting seat, both of the first connecting ring and the second connecting ring are fixedly connected to the guide rail, and a retaining ring is provided on the self-driving slider assembly. The self-driving slider assembly is fixedly connected to a retaining ring. A buffer rubber ring is provided on the retaining ring. By being equipped with a first connecting ring and a second connecting ring, the stability of the guide rail can be further improved and the guide rail can be prevented from being displaced. At the same time, it is equipped with a retaining ring, which can help keep the self-driven slider components of the same level highly consistent, making the operation more stable.

Preferably, the inner ring surface of the first connecting ring is inlaid with an infrared transmitting tube and an infrared receiving tube. The infrared receiving tube is electrically connected to the control device. The control device is fixedly connected to the first connecting ring. By configuring There are infrared transmitting tubes and infrared receiving tubes. Once the infrared rays are blocked by the multi-rotor drone, the infrared receiving tubes will feedback the information to the control device, which can effectively improve the degree of automation and make the operation more intelligent.

Preferably, the outer ring surface of the second connecting ring is provided with a first hinge joint, a second hinge joint and a third hinge joint, and the first hinge joint, the second hinge joint and the third hinge joint are all connected with the second hinge joint. The connecting ring is fixedly connected, and the first hinged joint, the second hinged joint and the third hinged joint are all provided with connecting legs, and the first hinged joint, the second hinged joint and the third hinged joint are connected with their respective The legs are connected by rotation. The connecting legs and the second connecting ring form a tripod structure. A base plate is provided below the connecting base. A connecting column is provided on the base plate. A connecting ball is provided at the top of the connecting column. On the connecting base There is a rotation hole that matches the connecting ball. The connecting column and the connecting seat are rotationally connected through the connecting ball and the rotating hole. It adopts a rotatable structure and can change the direction of the launch chamber according to actual needs, greatly improving flexibility. , and at the same time, it is equipped with a tripod structure, which can provide good support effect and effectively ensure the stability during operation.

Preferably, the self-driving slider assembly includes a slider body and a rack, the dovetail and the slider body are integrally arranged, and the dovetail is provided with a placement groove, an installation groove and an axis hole, and the The placement groove and the installation groove are connected through the shaft hole. There are two installation grooves. Each of the installation grooves is equipped with a brushless motor. The brushless motor is arranged horizontally opposite to each other. There is a brushless motor installed in the installation groove. The drive gear is matched with the rack. The end of the output shaft of the brushless motor passes through the shaft hole and is fixedly connected to the drive gear in the placement groove. The rack is in close contact with the bottom of the vertical guide groove and is in contact with the guide rail. Bolt connection, the brushless motor is electrically connected to the control device, using gear transmission, which has good stability. At the same time, the brushless motor is installed in a horizontally opposite manner, which not only ensures good gravity parallelism , and at the same time it can provide good power, and the independent driving structure makes the self-driving slider components of different levels have little influence on each other.

Preferably, the dovetail tenon and the vertical guide groove have a clearance fit, and a needle roller row is provided between the vertical guide groove and the dovetail tenon. The needle roller row is fixedly connected to the guide rail. The dovetail tenon and the needle roller row Close to each other, there are slew bearings on both sides of the drive gear. One side of the slew bearing is fixedly connected to the drive gear. The other side of the slew bearing is fixedly connected to the groove wall of the placement groove. An air inlet is provided on the side of the guide rail. , the air inlet holes are provided with more than one, the air inlet holes are distributed at equal intervals, the air inlet holes are connected with the vertical guide grooves, and are equipped with needle roller rows, which can effectively reduce the friction during operation. , it is also equipped with a turntable bearing, which can ensure the stability of the gear operation, reduce the vibration of the gear, and make the conveying work more stable. It is also equipped with an air inlet to allow the outside air to flow in when the self-driven slider assembly operates upward at high speed. Can be pressed into the vertical guide groove to cool down the brushless motor.

Preferably, the ejection device includes a carrier plate, a metal connecting piece and a connecting rope body, the metal connecting piece is embedded in the carrier plate, the slider body is provided with an insertion slot that matches the carrier plate, and the The carrier plate is rotatably connected to the slider body. A first electromagnet is embedded on the bottom of the insertion slot. A second electromagnet, a third electromagnet and a fourth electromagnet are arranged between the first electromagnet and the metal connecting piece. Electromagnet, the first electromagnet, the second electromagnet, the third electromagnet and the fourth electromagnet are all fixedly connected with the connecting rope body and form a fan-shaped distribution, the first electromagnet, the second electromagnet, the third electromagnet The electromagnet and the fourth electromagnet are both electrically connected to the control device. The outer surfaces of the first electromagnet, the second electromagnet, the third electromagnet and the fourth electromagnet are all coated with buffer silica gel layers, and multiple Electromagnets are used to launch multi-rotor drones. The ejection device has a simple structure and takes up little space.

Preferably, the adsorption mechanism includes an air pump and a sealing rubber ring. The inside of the carrier plate is hollow and forms a negative pressure chamber. The air nozzle of the air pump is connected to the negative pressure chamber. The carrier plate One end is provided with an air port. The sealing rubber ring is fixedly connected to the carrier plate and surrounds the air port. The air pump is electrically connected to the control device. The outside of the air pump is wrapped with a rubber sleeve. The adsorption mechanism has a simple structure and is easy to maintain. It is convenient, and at the same time, the outside of the air pump is wrapped with a rubber sleeve, which can effectively prevent the air pump from being damaged due to violent impact.

Preferably, the back side of the rack is embedded with a magnet, and the driving gear is a ferrite stainless steel gear. By inlaying a magnet on the back side of the rack, the driving gear can be absorbed, and the self-driving slider can be Components play a certain positioning effect.

The invention also provides a control method for a delivery device of a multi-rotor aircraft, which includes the following steps:

1) Place the multi-rotor drones on the sealing rubber ring of the carrier plate in sequence;

2) Start the air pump through the control device to pump the negative pressure chamber into a negative pressure state, so that the multi-rotor drone is adsorbed;

3) Start the brushless motor through the control device to quickly transport the multi-rotor drone to the top of the launch bay;

4) Once the infrared ray is blocked by the multi-rotor drone, the infrared receiving tube will feedback the information to the control device, and then the control device stops the work of the brushless motor and air pump, and starts the fourth electromagnet, the third electromagnet, and the third electromagnet in sequence. The second electromagnet and the first electromagnet are started sequentially with an interval of 0.25s, so that the carrier plate is quickly embedded into the embedding slot, causing the multi-rotor drone to be thrown out of the launch chamber, completing the launch of a drone.

The beneficial effects of the present invention are: multiple multi-rotor drones can be stacked on self-driven slider assemblies of different levels in sequence, and the control device can be used to control the multiple drones to be launched in sequence. When multiple multi-rotor drones are needed, In the case of a plane, it can reduce the need for a take-off location and reduce the placement time.

Description of the drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can also be obtained based on these drawings without exerting creative efforts.

Figure 1 is a schematic diagram of the overall structure of a delivery device for a multi-rotor aircraft according to the present invention.

Figure 2 is a partial structural schematic diagram of a delivery device for a multi-rotor aircraft according to the present invention.

Figure 3 is a perspective view of a self-driven slider assembly used in a delivery device for a multi-rotor aircraft according to the present invention.

Figure 4 is a cross-sectional view of a self-driven slider assembly used in a delivery device for a multi-rotor aircraft according to the present invention.

In the picture:

1. Connecting seat; 2. Control device; 3. Guide rail; 4. Launch chamber; 5. Self-driven slide assembly; 6. Dovetail; 7. Vertical guide groove; 8. Ejection device; 9. First connecting ring ; 10. Second connecting ring; 11. Retaining ring; 12. Infrared receiving tube; 13. First hinged joint; 14. Second hinged joint; 15. Connecting feet; 16. Bottom plate; 17. Connecting column; 18. Connection Ball; 19. Slider body; 20. Rack; 21. Installation groove; 22. Installation groove; 23. Brushless motor; 24. Driving gear; 25. Needle roller row; 26. Rotary plate bearing; 27. Air inlet ; 28. Carrier plate; 29. Metal connecting piece; 30. Connecting rope body; 31. Insertion slot; 32. First electromagnet; 33. First electromagnet; 34. Third electromagnet; 35. Fourth electromagnet ; 36. Air pump; 37. Sealing rubber ring; 38. Magnet body.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, rather than all the embodiments.

In the embodiments, it should be understood that the terms "middle", "upper", "lower", "top", "right side", "left end", "upper", "back", "middle", etc. indicate The orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, Therefore, it should not be construed as a limitation of the present invention.

In addition, unless the connection or fixation method between the components is specifically described in this embodiment, the connection or fixation method can be by bolts commonly used in the prior art, or pins, pins, or pins. Conventional methods such as adhesive fixation or riveting fixation will not be described in detail in the embodiments.

Example

As shown in Figures 1-4, a delivery device for a multi-rotor aircraft includes a connecting base 1 and a control device 2. The connecting base 1 is provided with a guide rail 3, and the guide rail 3 is provided with more than one. The guide rails 3 are distributed in an annular array and form a launch bay 4 that matches the multi-rotor UAV. The guide rail 3 is fixedly connected to the connecting base 1. The guide rail 3 is provided with a launcher for transporting the multi-rotor UAV to the launch site. The self-driven slider assembly 5 at the top of the warehouse 4 is provided with a dovetail tenon 6. The guide rail 3 is provided with a vertical guide groove 7 that matches the dovetail tenon 6. The self-driven slider assembly 5 is provided with a dovetail tenon 6. The slider assembly 5 is slidingly connected to the guide rail 3 through the vertical guide groove 7. There are more than one self-driven slider assembly 5, and the fronts of the self-driven slider assembly 5 are equipped with ejectors for ejecting the multi-rotor drone. Device 8. The ejection device 8 is located in the launch chamber 4. The ejection device 8 is provided with an adsorption mechanism for adsorbing the multi-rotor UAV during transportation. The self-driven slider assembly 5, the ejection device 8 and The adsorption mechanisms are all electrically connected to the control device 2 .

In this embodiment, a first connecting ring 9 and a second connecting ring 10 are provided above the connecting seat 1. Both the first connecting ring 9 and the second connecting ring 10 are fixedly connected to the guide rail 3. The self-driven The slider assembly 5 is provided with a retaining ring 11. The self-driving slider assembly 5 is fixedly connected to the retaining ring 11. A buffer rubber ring (not shown) is provided on the retaining ring 11, and a first connecting ring is provided through the retaining ring 11. 9 and the second connecting ring 10 can further improve the stability of the guide rail 3 and prevent the guide rail 3 from being displaced. At the same time, the retaining ring 11 can help to maintain the same height of the self-driven slider assembly 5 of the same level, so that Operation is more stable.

In this embodiment, an infrared transmitting tube (not shown) and an infrared receiving tube 12 are embedded on the inner ring surface of the first connecting ring 9. The infrared receiving tube 12 is electrically connected to the control device 2. The control device 2 is fixedly connected to the first connection ring 9 and is equipped with an infrared transmitting tube and an infrared receiving tube 12. Once the infrared rays are blocked by the multi-rotor drone, the infrared receiving tube 12 will feedback the information to the control device 2, which can effectively Improve the degree of automation and make operations more intelligent.

In this embodiment, the outer ring surface of the second connecting ring 10 is provided with a first hinge joint 13 , a second hinge joint 14 and a third hinge joint (not shown). The second hinge joint 14 and the third hinge joint are both fixedly connected to the second connecting ring 10. The first hinge joint 13, the second hinge joint 14 and the third hinge joint are all provided with connecting feet 15. The first hinge joint The head 13, the second hinge joint 15 and the third hinge joint are all rotationally connected with their respective connecting legs 15. The connecting legs 15 and the second connecting ring 10 constitute a tripod structure. A bottom plate 16 is provided below the connecting seat 1. The bottom plate 16 is provided with a connecting post 17, and the top of the connecting post 17 is provided with a connecting ball 18. The connecting seat 1 is provided with a rotation hole (not shown) that matches the connecting ball 18. The connecting post 17 17 and the connecting base 1 are rotationally connected through the connecting ball 18 and the rotating hole. It adopts a rotatable structure, which can change the direction of the launch chamber according to actual needs, greatly improving flexibility. At the same time, it is equipped with a tripod structure, which can provide good The support effect can effectively ensure the stability during operation.

In this embodiment, the self-driving slider assembly 5 includes a slider body 19 and a rack 20 . The dovetail 6 and the slider body 19 are integrally arranged. There is a placement groove on the dovetail 6 . 21. Installation groove 22 and shaft hole (not shown). The installation groove 21 and the installation groove 22 are connected through the shaft hole. There are two installation grooves 22, and there are brushless brushes in each installation groove 22. Motor 23. The brushless motor 23 is arranged horizontally opposite. A driving gear 24 matched with the rack 20 is provided in the placement groove 21. The end of the output shaft of the brushless motor 22 passes through the shaft hole and is connected with the shaft hole. The driving gear 24 in the placement slot 21 is fixedly connected. The rack 20 is in close contact with the bottom of the vertical guide slot 7 and bolted to the guide rail 3. The brushless motor 23 is electrically connected to the control device 2, using a The gear transmission method has good stability. At the same time, the brushless motor is installed in a horizontally opposed manner, which not only ensures good gravity parallelism, but also provides good power. At the same time, the separate drive structure makes each different The self-driven slider components of the hierarchy have little interaction with each other.

In this embodiment, the dovetail 6 and the vertical guide groove 7 have a clearance fit, and a needle roller row 25 is provided between the vertical guide groove 7 and the dovetail 6 , and the needle roller row 25 is fixed to the guide rail 3 connection, the dovetail tenon 6 is in close contact with the needle roller row 25, and turntable bearings 26 are provided on both sides of the drive gear 24. One side of the turntable bearing 26 is fixedly connected to the drive gear 24, and the other side of the turntable bearing 26 is fixedly connected to the drive gear 24. The groove walls of the placement groove are fixedly connected. An air inlet 27 is provided on the side of the guide rail 3. There are more than one air inlets 27. The air inlets 27 are equally spaced and arranged vertically. The guide grooves 7 are connected, and are equipped with needle roller rows 25, which can effectively reduce friction during operation. At the same time, they are equipped with turntable bearings 26, which can ensure the stability of gear operation, reduce gear jitter, and make the conveying work more efficient. Stablize.

In this embodiment, the ejection device 8 includes a carrier plate 28, a metal connecting piece 29 and a connecting rope body 30. The metal connecting piece 29 is embedded in the carrier plate 28, and the slider body 19 is provided with a The insertion slot 31 is matched with the carrier plate 28. The carrier plate 28 is rotationally connected to the slider body 19. A first electromagnet 32 is embedded in the bottom of the insertion slot 31. The first electromagnet 32 is connected to the metal. A second electromagnet 33, a third electromagnet 34 and a fourth electromagnet 35 are arranged between the pieces 29. The first electromagnet 32, the second electromagnet 33, the third electromagnet 34 and the fourth electromagnet 35 are all Fixedly connected to the connecting rope body 30 and forming a fan-shaped distribution, the first electromagnet 32, the second electromagnet 33, the third electromagnet 34 and the fourth electromagnet 35 are all electrically connected to the control device 2. The outer surfaces of the electromagnet 32, the second electromagnet 33, the third electromagnet 34 and the fourth electromagnet 35 are all coated with a buffer silica gel layer (not shown), and multiple electromagnets are used to launch the multi-rotor drone. , the ejection device has a simple structure and takes up less space.

In this embodiment, the adsorption mechanism includes an air pump 36 and a sealing rubber ring 37. The carrier plate 28 is hollow and has a negative pressure chamber (not shown). The mouth is connected with the negative pressure chamber. One end of the carrier plate 28 is provided with an air port (not shown). The sealing rubber ring 37 is fixedly connected to the carrier plate 28 and surrounds the air port. The air pump 36 is electrically connected to the control device. Sexual connection, the outer surface of the air pump 36 is wrapped with a rubber sleeve (not shown), the adsorption mechanism has a simple structure and is easy to maintain. At the same time, the outer surface of the air pump 36 is wrapped with a rubber sleeve, which can effectively prevent the air pump from being hit by a violent impact. cause damage.

In this embodiment, a magnet 38 is embedded on the back of the rack 20, and the driving gear is a ferrite stainless steel gear. The magnet 38 is embedded on the back of the rack, which can absorb the driving gear. It has a certain positioning effect on the self-driven slider assembly.

The invention also provides a control method for a delivery device of a multi-rotor aircraft, which includes the following steps:

1) Place the multi-rotor drones on the sealing rubber ring of the carrier plate in sequence;

2) Start the air pump through the control device to pump the negative pressure chamber into a negative pressure state, so that the multi-rotor drone is adsorbed;

3) Start the brushless motor through the control device to quickly transport the multi-rotor drone to the top of the launch bay;

4) Once the infrared ray is blocked by the multi-rotor drone, the infrared receiving tube will feedback the information to the control device, and then the control device stops the work of the brushless motor and air pump, and starts the fourth electromagnet, the third electromagnet, and the third electromagnet in sequence. The second electromagnet and the first electromagnet are started sequentially with an interval of 0.25s, so that the carrier plate is quickly embedded into the embedding slot, causing the multi-rotor drone to be thrown out of the launch chamber, completing the launch of a drone.

The beneficial effects of the present invention are: multiple multi-rotor drones can be stacked on self-driven slider assemblies of different levels in sequence, and the control device can be used to control the multiple drones to be launched in sequence. When multiple multi-rotor drones are needed, In the case of a plane, it can reduce the need for a take-off location and reduce the placement time.

The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that are not thought of through creative efforts should be covered by the protection scope of the present invention.

Claims (6)

1. A put in device for many rotor crafts, its characterized in that: the automatic-driving unmanned aerial vehicle comprises a connecting seat and a control device, wherein a guide rail is arranged on the connecting seat, the guide rail is provided with more than one, the guide rail is distributed in an annular array and is provided with a transmitting bin matched with the multi-rotor unmanned aerial vehicle, the guide rail is fixedly connected with the connecting seat, a self-driving sliding block assembly used for conveying the multi-rotor unmanned aerial vehicle to the top end of the transmitting bin is arranged on the guide rail, a dovetail joint is arranged on the self-driving sliding block assembly, a vertical guide groove matched with the dovetail joint is arranged on the guide rail, the self-driving sliding block assembly is in sliding connection with the guide rail through the vertical guide groove, the self-driving sliding block assembly is provided with more than one, the front surface of the self-driving sliding block assembly is provided with an ejecting device for ejecting the multi-rotor unmanned aerial vehicle, the ejecting device is positioned in the transmitting bin, an adsorption mechanism used for adsorbing the multi-rotor unmanned aerial vehicle in conveying is arranged on the ejecting device, and the self-driving sliding block assembly, the ejecting device and the adsorption mechanism are electrically connected with the control device;

the self-driven sliding block assembly comprises a sliding block body and a rack, wherein the dovetail and the sliding block body are integrally arranged, a mounting groove and a shaft hole are formed in the dovetail, the mounting groove and the mounting groove are communicated through the shaft hole, two mounting grooves are formed in the mounting groove, brushless motors are arranged in the mounting groove in a horizontally opposite mode, driving gears matched with the rack are arranged in the mounting groove, the tail end of an output shaft of the brushless motor penetrates out of the shaft hole and is fixedly connected with the driving gears in the mounting groove, the rack is tightly attached to the bottom of a vertical guide groove and is connected with a guide rail bolt, and the brushless motors are electrically connected with a control device;

the ejection device comprises a carrier plate, a metal connecting sheet and a connecting rope body, wherein the metal connecting sheet is embedded in the carrier plate, an insertion groove matched with the carrier plate is formed in the slider body, the carrier plate is rotationally connected with the slider body, a first electromagnet is embedded on the bottom of the insertion groove, a second electromagnet, a third electromagnet and a fourth electromagnet are arranged between the first electromagnet and the metal connecting sheet, the first electromagnet, the second electromagnet, the third electromagnet and the fourth electromagnet are fixedly connected with the connecting rope body and form fan-shaped distribution, the first electromagnet, the second electromagnet, the third electromagnet and the fourth electromagnet are electrically connected with the control device, and buffer silica gel layers are coated on the outer surfaces of the first electromagnet, the second electromagnet, the third electromagnet and the fourth electromagnet;

the adsorption mechanism comprises an air pump and a sealing rubber ring, a negative pressure cavity is formed in the support plate, an air suction nozzle of the air pump is communicated with the negative pressure cavity, an air port is formed in one end of the support plate, the sealing rubber ring is fixedly connected with the support plate and surrounds the air port, the air pump is electrically connected with the control device, and a rubber sleeve is wrapped on the outer side of the air pump.

2. A launch device for a multi-rotor aircraft according to claim 1, characterized in that: the connecting seat top is provided with first go-between and second go-between, first go-between and second go-between all with guide rail fixed connection, be provided with the holding ring on the self-driven slider subassembly, self-driven slider subassembly and holding ring fixed connection, be provided with the buffer rubber circle above the holding ring.

3. A launch apparatus for a multi-rotor aircraft according to claim 2 wherein: the infrared transmitting tube and the infrared receiving tube are embedded on the inner ring surface of the first connecting ring, the infrared receiving tube is electrically connected with the control device, and the control device is fixedly connected with the first connecting ring.

4. A launch apparatus for a multi-rotor aircraft according to claim 3 wherein: the outer ring surface of second go-between is provided with first articulated joint, second articulated joint and third articulated joint, first articulated joint, second articulated joint and third articulated joint all with second go-between fixed connection, all be provided with the connecting leg on first articulated joint, second articulated joint and the third articulated joint, first articulated joint, second articulated joint and third articulated joint all rotate with the connecting leg on their each and are connected, connecting leg and second go-between constitute tripod structure, the connecting seat below is provided with the bottom plate, be provided with the spliced pole on the bottom plate, the spliced pole top is provided with the spliced ball, be provided with the rotation hole that matches with the spliced ball on the connecting seat, spliced pole and connecting seat pass through spliced ball and rotation hole rotation connection.

5. A launch apparatus for a multi-rotor aircraft according to claim 4 wherein: the novel rolling needle is characterized in that the dovetail is in clearance fit with the vertical guide groove, a rolling needle row is arranged between the vertical guide groove and the dovetail, the rolling needle row is fixedly connected with the guide rail, the dovetail is clung to the rolling needle row, two sides of the driving gear are respectively provided with a turntable bearing, one face of each turntable bearing is fixedly connected with the driving gear, the other face of each turntable bearing is fixedly connected with the groove wall of the corresponding mounting groove, an air inlet is formed in the side face of the guide rail, more than one air inlet hole is formed in the side face of the guide rail, the air inlet holes are distributed at equal intervals, and the air inlet holes are communicated with the vertical guide groove.

6. A method for controlling a launch device for a multi-rotor aircraft, comprising the steps of:

1) Sequentially placing the multi-rotor unmanned aerial vehicle on a sealing rubber ring of a carrier plate;

2) Starting an air pump through a control device to pump the negative pressure cavity into a negative pressure state, so that the multi-rotor unmanned aerial vehicle is adsorbed;

3) Starting a brushless motor through a control device, and rapidly conveying the multi-rotor unmanned aerial vehicle to the top end of the launching bin;

4) Once the infrared ray is shielded by many rotor unmanned aerial vehicle, the infrared ray receiver tube gives controlling means with information feedback, and controlling means stops brushless motor and air pump's work afterwards to start fourth electro-magnet, third electro-magnet, second electro-magnet and first electro-magnet in proper order, start the interval in proper order and be 0.25s, make the carrier plate embed into the embedded groove fast, lead to many rotor unmanned aerial vehicle to be thrown out the emission storehouse, accomplish the input of an unmanned aerial vehicle.