Unmanned aerial vehicle launching and control device

Abstract

The invention discloses an unmanned aerial vehicle launching and control device, and relates to the unmanned attack and self-defense field, the unmanned aerial vehicle launching and control device comprises a box body, a launching system and a control system, the launching system is arranged in the box body, the launching system comprises a supporting mechanism, a launching track and an electromagnetic attraction mechanism, the launching track is arranged on the upper part of the supporting mechanism, and the electromagnetic attraction mechanism is arranged on the launching track; the unmanned aerial vehicle is placed on the launching track, the electromagnetic attraction mechanism is arranged on the upper portion of the supporting mechanism and can attract the unmanned aerial vehicle when powered on, and the electromagnetic attraction mechanism and the unmanned aerial vehicle are both in signal connection with the control system. The unmanned aerial vehicle launching and control device can realize attack and defense capabilities of armored vehicles, ships and large aircrafts, and reduces the risk of exposure of a platform or a launching position.

Description

Technical Field

[0001] The invention relates to the field of unmanned attack and self-defense, and in particular to a launching and controlling device for an unmanned aerial vehicle. Background Art

[0002] When launching unmanned aerial vehicles, various existing armored vehicles, ships, large aircraft and other platforms need to use airbags or rocket engines (a general term for rocket boosters, rocket thrusters, small rocket engines, micro rocket engines, etc.) to propel the unmanned aerial vehicles. The use of airbags will produce a loud noise, and the use of rocket engines will produce launch smoke, which can easily lead to the exposure of the platform or launch position and poor concealment. Summary of the invention

[0003] In order to solve the above technical problems, the present invention provides an unmanned aerial vehicle launch and control device, which can realize the attack and defense capabilities of armored vehicles, ships, and large aircraft, and reduce the risk of exposure of platforms or launch positions.

[0004] To achieve the above object, the present invention provides the following solutions:

[0005] The present invention provides an unmanned aerial vehicle launch and control device, comprising a box, a launch system and a control system. The launch system is used to be arranged in the box, and the launch system comprises a support mechanism, a launch track and an electromagnetic suction mechanism. The launch track is arranged on the upper part of the support mechanism, and the unmanned aerial vehicle is placed on the launch track. The electromagnetic suction mechanism is arranged on the upper part of the support mechanism. The electromagnetic suction mechanism can absorb the unmanned aerial vehicle when powered on, and the electromagnetic suction mechanism and the unmanned aerial vehicle are both connected to the control system signal.

[0006] Preferably, when the electromagnetic suction mechanism is powered on, it can absorb the rotating component at the rear end of the UAV without affecting the rotation of the rotating component of the UAV.

[0007] Preferably, the electromagnetic suction mechanism includes a shell, a rotating connection assembly and an electromagnetic suction component. The shell is fixed to the upper part of the support mechanism. The electromagnetic suction component is connected to the shell through the rotating connection assembly. When the electromagnetic suction component is energized, it can absorb the rotating component at the rear end of the unmanned aerial vehicle without affecting the rotation of the rotating component of the unmanned aerial vehicle. The control system is used to control the power on or off of the electromagnetic suction component.

[0008] Preferably, it also includes a docking piece, which is used to be fixed on the rotating component at the rear end of the unmanned aerial vehicle. The docking piece can dock with the electromagnetic suction component, so that the axis around which the docking piece and the rotating component of the unmanned aerial vehicle rotate is colinear with the axis around which the electromagnetic suction component rotates, and the circumferential relative movement of the docking piece and the electromagnetic suction component is restricted, and the electromagnetic suction component can adsorb the docking piece when energized.

[0009] Preferably, the electromagnetic suction component includes an electromagnetic suction column and an electromagnetic suction plate arranged at one end of the electromagnetic suction column, the rotating connection assembly includes a rolling bearing and a plane bearing, the inner ring of the rolling bearing is fixedly sleeved on the outside of the electromagnetic suction column, the plane bearing is fixedly sleeved on the outside of the outer ring of the rolling bearing, the plane bearing is fixed in the shell, the rolling body of the plane bearing is in contact with one side of the electromagnetic suction plate, and the other side of the electromagnetic suction plate is provided with a docking groove matching the docking piece structure, and the docking piece can be docked with the electromagnetic suction plate through the docking groove.

[0010] Preferably, the docking member includes a disc and a positioning block arranged around the disc, the central axis of the disc is arranged colinearly with the central axis of the rotating component of the unmanned aerial vehicle, the docking groove includes a circular groove and a positioning groove arranged around the circular groove, the disc is used to extend into the circular groove, and the positioning block is used to extend into the positioning groove.

[0011] Preferably, the electromagnetic suction plate is a circular plate, the electromagnetic suction column is a circular column, the central axis of the electromagnetic suction column is collinear with the central axis of the electromagnetic suction plate, and the central axis of the circular groove is collinear with the central axis of the electromagnetic suction plate.

[0012] Preferably, the launch track includes two track assemblies, and the two track assemblies are arranged in parallel on the upper part of the support mechanism; the track assembly includes a first track, a second track and a locking component, the first track is fixed on the support mechanism, the second track is slidably installed on the first track, and the locking component can lock and fix the second track on the first track.

[0013] Preferably, the support mechanism includes a first support member, a second support member and an angle adjustment mechanism, the second support member is hinged to the first support member and is located above the first support member, the angle adjustment mechanism is used to adjust the angle between the second support member and the first support member, and the launch track and the electromagnetic suction mechanism are both arranged on the upper part of the second support member.

[0014] Preferably, the angle adjustment mechanism includes a plurality of angle adjustment components, the angle adjustment components include a plurality of angle adjustment blocks, the bottom surface and the top surface of the angle adjustment blocks are respectively used to fit with the upper portion of the first support member and the lower portion of the second support frame, the angles between the bottom surface and the top surface of all the angle adjustment blocks in each of the angle adjustment components are the same, and the angle between the bottom surface and the top surface of the angle adjustment block of one angle adjustment component is different from the angle between the bottom surface and the top surface of the angle adjustment block of another angle adjustment component.

[0015] Compared with the prior art, the present invention has achieved the following technical effects:

[0016] The unmanned aerial vehicle launch and control device of the present invention comprises a box, a launch system and a control system, wherein the launch system comprises a support mechanism, a launch track and an electromagnetic suction mechanism, and the launch track is used to place the unmanned aerial vehicle. In the initial state, the unmanned aerial vehicle and the launch system are both arranged in the box. When in use, the support mechanism is installed on the platform of an armored vehicle, a ship or a large aircraft, the box is removed, and the control system controls the electromagnetic suction mechanism to be energized, thereby adsorbing the unmanned aerial vehicle, and then the rotating part of the unmanned aerial vehicle rotates, and after reaching the take-off flight threshold by relying on the power of the unmanned aerial vehicle itself, the electromagnetic suction mechanism is controlled to be powered off, and at this time, the unmanned aerial vehicle slides on the launch track to complete the launch. It can be seen that in the service state, as a structural member integrating storage, transportation and launch of the unmanned aerial vehicle, in the combat state, it can be directly connected to the platform to complete the launch function, thereby realizing the attack and defense capabilities of armored vehicles, ships and large aircraft, and at the same time, it is generally applicable to all pre-set launch systems in underwater, land, jungle, underground fortifications and other building structures that need to be concealed for launch. In addition, the launch function of unmanned aerial vehicles can be achieved without the aid of other power sources, reducing the risk of exposing the platform or launch position due to sound and launch smoke dispersion, thereby improving concealment. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 A schematic diagram of the use of the unmanned aerial vehicle launch and control device provided by the present invention;

[0019] Figure 2 A schematic diagram of the docking of a docking piece and an electromagnetic suction plate in the unmanned aerial vehicle launch and control device provided by the present invention;

[0020] Figure 3This is a schematic structural diagram of the electromagnetic suction component and the rotating connection assembly in the unmanned aerial vehicle launching and control device provided by the present invention.

[0021] Explanation of the accompanying drawings: 1. First support member; 2. Second support member; 3. Angle adjustment block; 4. First track; 5. Second track; 6. Locking component; 7. Unmanned aerial vehicle; 8. Rotating component; 9. Docking member; 10. Shell; 11. Electromagnetic suction column; 12. Electromagnetic suction plate; 13. Rolling bearing; 14. Plane bearing. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] The purpose of the present invention is to provide an unmanned aerial vehicle launch and control device, which can realize the attack and defense capabilities of armored vehicles, ships, and large aircraft, and reduce the risk of exposure of the platform or launch position.

[0024] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0025] like Figure 1-Figure 3 As shown, this embodiment provides an unmanned aerial vehicle launch and control device, including a box, a launch system and a control system. The launch system is used to be set in the box. The launch system includes a supporting mechanism, a launching track and an electromagnetic suction mechanism. The launching track is arranged on the upper part of the supporting mechanism. The launching track is used to place the unmanned aerial vehicle 7. The electromagnetic suction mechanism is arranged on the upper part of the supporting mechanism. The electromagnetic suction mechanism can absorb the unmanned aerial vehicle 7 when powered on. The electromagnetic suction mechanism and the unmanned aerial vehicle 7 are both connected to the control system signal.

[0026] In the initial state, the unmanned aerial vehicle 7 and the launching system are both arranged in a box. When in use, the supporting mechanism is installed on the platform of an armored vehicle, ship or large aircraft, the box is removed, and the control system controls the electromagnetic suction mechanism to be energized, thereby adsorbing the unmanned aerial vehicle 7. After that, the rotating part 8 of the unmanned aerial vehicle 7 rotates, and after reaching the take-off flight threshold by relying on the power of the unmanned aerial vehicle 7 itself, the electromagnetic suction mechanism is controlled to be powered off. At this time, the unmanned aerial vehicle 7 slides on the launching track to complete the launch.

[0027] It can be seen that when in service state, as a structural component for storage, transportation and launching of unmanned aerial vehicles 7, in combat state, it can be directly connected to the platform to complete the launch function, thereby realizing the attack and defense capabilities of armored vehicles, ships, and large aircraft. At the same time, it is applicable to all pre-set launch systems in underwater, land, jungle, underground fortifications and other building structures that require concealed launch. In addition, the power source of the launched unmanned aerial vehicle is the power of the unmanned aerial vehicle itself. Without the help of other power, the launch function of the unmanned aerial vehicle 7 is realized, reducing the risk of exposure of the platform or launch position due to sound and launch smoke dispersion, and improving concealment.

[0028] When the rotating part 8 of the unmanned aerial vehicle 7 is arranged at the front end of the aircraft body, the electromagnetic suction mechanism is arranged at the rear end of the upper part of the supporting mechanism and is located at the rear end of the unmanned aerial vehicle 7. When the electromagnetic suction mechanism is powered on, it can adsorb the rear end of the unmanned aerial vehicle 7.

[0029] When the rotating part 8 of the unmanned aerial vehicle 7 is arranged at the rear end of the aircraft body, the electromagnetic suction mechanism is arranged at the rear end of the upper part of the supporting mechanism and is located at the rear end of the unmanned aerial vehicle 7. When the electromagnetic suction mechanism is energized, it can absorb the rotating part 8 at the rear end of the unmanned aerial vehicle 7 without affecting the rotation of the rotating part 8 of the unmanned aerial vehicle 7.

[0030] The UAV launch and control device in this embodiment is mainly used for the launch and control of all small, medium and micro UAVs 7, and is particularly suitable for small, medium and micro UAVs 7 that use head pull or tail rotor as the main thrust.

[0031] Specifically, the electromagnetic suction mechanism includes a shell 10, a rotating connection assembly and an electromagnetic suction component. The shell 10 is fixed to the upper part of the supporting mechanism. The electromagnetic suction component is connected to the shell 10 through the rotating connection assembly, so that the electromagnetic suction component can rotate relative to the shell 10. When the electromagnetic suction component is energized, it can absorb the rotating component 8 at the rear end of the unmanned aerial vehicle 7 without affecting the rotation of the rotating component 8 of the unmanned aerial vehicle 7. The electromagnetic suction component can rotate with the rotating component 8 of the unmanned aerial vehicle 7. The control system is used to control the electromagnetic suction component to be energized or de-energized.

[0032] The electromagnetic suction mechanism also includes a power supply module for supplying power to the electromagnetic suction component. The power supply module is connected to the control system signal. The control system controls the power supply module to power on or off the electromagnetic suction component.

[0033] In this embodiment, the shell 10 is fixed to the rear end of the upper part of the supporting mechanism, and an opening is provided at the front end of the shell 10. The rotating connection component is installed in the shell 10 through the opening. When the electromagnetic suction component is energized, it can absorb the rotating component 8 of the unmanned aerial vehicle 7. By setting the rotating connection component, the electromagnetic suction component does not affect the rotation of the rotating component 8 of the unmanned aerial vehicle 7.

[0034] like Figure 2 As shown, the present embodiment also includes a docking piece 9, which is used to be fixed on the rotating component 8 at the rear end of the unmanned aerial vehicle 7. The docking piece 9 can dock with the electromagnetic suction component, so that the axis around which the docking piece 9 and the rotating component 8 of the unmanned aerial vehicle 7 rotate is colinear with the axis around which the electromagnetic suction component rotates, and the circumferential relative movement of the docking piece 9 and the electromagnetic suction component is restricted, that is, after docking, the docking piece 9 and the electromagnetic suction component will not produce circumferential relative movement, and the electromagnetic suction component can adsorb the docking piece 9 when energized.

[0035] In this embodiment, the rotating component 8 at the rear end of the unmanned aerial vehicle 7 includes a rotating shaft and blades arranged on the rotating shaft. The docking member 9 is used to be fixed on the rotating shaft, and the central axis of the docking member 9 is arranged colinearly with the central axis of the rotating shaft.

[0036] like Figure 3 As shown, the electromagnetic suction component includes an electromagnetic suction column 11 and an electromagnetic suction plate 12 arranged at one end of the electromagnetic suction column 11, and the rotating connection assembly includes a rolling bearing 13 and a plane bearing 14. The inner ring of the rolling bearing 13 is fixedly sleeved on the outside of the electromagnetic suction column 11, and the plane bearing 14 is fixedly sleeved on the outside of the outer ring of the rolling bearing 13. The plane bearing 14 is fixed in the housing 10, and the rolling body of the plane bearing 14 is in contact with one side of the electromagnetic suction plate 12. The electromagnetic suction component is rotatably installed by arranging the rolling bearing 13 and the plane bearing 14, so that the electromagnetic suction component can rotate smoothly. The other side of the electromagnetic suction plate 12 is provided with a docking groove that matches the structure of the docking piece 9, and the docking piece 9 can dock with the electromagnetic suction plate 12 through the docking groove.

[0037] In this embodiment, the electromagnetic suction plate 12 is located at the front end of the electromagnetic suction column 11, the rolling element of the front end surface of the plane bearing 14 contacts the rear end surface of the electromagnetic suction plate 12, and the front end surface of the electromagnetic suction plate 12 is provided with a docking groove.

[0038] Specifically, the docking member 9 includes a disc and a positioning block disposed around the disc, and the central axis of the disc is disposed in a colinear relationship with the central axis of the rotating component 8 of the unmanned aerial vehicle 7. The docking groove includes a circular groove and a positioning groove disposed around the circular groove, the disc is used to extend into the circular groove, and the positioning block is used to extend into the positioning groove, so that after the docking member 9 is docked with the electromagnetic suction plate 12 through the docking groove, the circumferential relative movement of the docking member 9 and the electromagnetic suction plate 12 is restricted.

[0039] In this embodiment, the docking member 9 includes two positioning blocks symmetrically arranged on both sides of the disc, and the docking groove includes two positioning grooves symmetrically arranged on both sides of the circular groove, and each positioning block is used to extend into a positioning groove.

[0040] In this specific embodiment, the electromagnetic suction plate 12 is a circular plate, the electromagnetic suction column 11 is a circular column, the central axis of the electromagnetic suction column 11 is collinear with the central axis of the electromagnetic suction plate 12, and the central axis of the circular groove is collinear with the central axis of the electromagnetic suction plate 12. After the circular plate of the docking member 9 is docked with the circular groove of the docking groove, the axis around which the docking member 9 and the rotating component 8 of the unmanned aerial vehicle 7 rotate is collinear with the axis around which the electromagnetic suction component rotates.

[0041] In this specific embodiment, the electromagnetic suction plate 12 and the electromagnetic suction column 11 are both made of electromagnet material, and the docking member 9 is made of ferromagnetic material.

[0042] Specifically, a cable is provided at the rear end of the electromagnetic suction column 11 to connect with the power supply module to realize power supply. When the electromagnetic suction column 11 rotates, the cable will be driven to rotate. Therefore, a reverse rotating motor is provided to drive the cable to rotate in the reverse direction, thereby offsetting the motion torque and avoiding cable entanglement and damage.

[0043] Specifically, the control system controls the flight of the unmanned aerial vehicle 7 by wireless remote control. The control system controls the electromagnetic suction component to be powered on or off by wireless or wired instructions.

[0044] In this specific embodiment, the control system controls the unmanned aerial vehicle 7 and the electromagnetic suction component through wireless commands, and can use a ground station and wireless control to achieve the role of weapon ambush and pre-positioning.

[0045] The launching track in this embodiment includes two track components, and the two track components are arranged in parallel on the upper part of the supporting mechanism.

[0046] The length of the track assembly in this embodiment is adjustable. Specifically, the track assembly includes a first track 4, a second track 5 and a locking component 6. The first track 4 is fixed to the supporting mechanism, the second track 5 is slidably installed on the first track 4, and the locking component 6 can lock and fix the second track 5 to the first track 4.

[0047] When in use, in order to lengthen the track assembly, the locking component 6 is turned so that it no longer locks the second track 5 and the first track 4, and the second track 5 is pulled outward to increase the overall length of the track assembly, and then the second track 5 and the first track 4 are locked by the locking component 6.

[0048] In this specific embodiment, the first rail 4 and the second rail 5 are both made of channel steel, that is, the cross-sections of the first rail 4 and the second rail 5 are both U-shaped structures, and the second rail 5 is slidably installed in the U-shaped groove of the first rail 4. The locking component 6 is a locking bolt, and locking bolts are provided on both sides of the first rail 4. The locking bolts are threadedly installed on one side of the first rail 4, and can extend between the first rail 4 and the second rail 5, and press against the outside of one side of the second rail 5, thereby realizing the locking of the second rail 5 and the first rail 4.

[0049] The support mechanism in this embodiment includes a first support member 1, a second support member 2 and an angle adjustment mechanism, wherein the first support member 1 is used to be installed on a platform of an armored vehicle, a ship or a large aircraft, and the second support member 2 is hinged to the first support member 1 and is located above the first support member 1. Specifically, the rear end of the second support member 2 is hinged to the rear end of the first support member 1. The angle adjustment mechanism is used to adjust the angle between the second support member 2 and the first support member 1, and the launch track and the electromagnetic suction mechanism are both arranged on the upper part of the second support member 2.

[0050] In this embodiment, the first rail 4 and the shell 10 are both arranged on the upper part of the second support member 2. Specifically, the shell 10 is arranged at the center of the upper rear end of the second support member 2, and the two first rails 4 are symmetrically arranged on both sides of the shell 10. The second rail 5 can extend from the front end of the first rail 4 to achieve adjustment of the length of the rail assembly.

[0051] Specifically, the angle adjustment mechanism includes multiple angle adjustment components, and the angle adjustment components include multiple angle adjustment blocks 3. The bottom surface and top surface of the angle adjustment block 3 are respectively used to fit with the upper part of the first support member 1 and the lower part of the second support frame. The angles between the bottom surface and the top surface of all the angle adjustment blocks 3 in each angle adjustment component are the same, and the angle between the bottom surface and the top surface of the angle adjustment block 3 of one angle adjustment component is different from the angle between the bottom surface and the top surface of the angle adjustment block 3 of another angle adjustment component.

[0052] By replacing different angle adjustment components, the angle between the second support member 2 and the first support member 1 can be adjusted, and then the angle between the second support member 2 and the first support member 1 can be adjusted according to the flight angle required by the unmanned aerial vehicle 7.

[0053] Specifically, the first support member 1 and the second support member 2 may be in the shape of a flat plate, a trident, or a parallelogram.

[0054] In this specific embodiment, the first support member 1 is a first support plate, which includes a first middle plate and two support plates respectively arranged at the front ends of both sides of the first middle plate. The second support member 2 is a second support plate, which includes a second middle plate and support plates respectively arranged at the front ends of both sides of the second middle plate. The rear end of the second middle plate is hinged to the rear end of the first middle plate, the housing 10 is fixed to the middle of the second middle plate, and the two first rails 4 are respectively fixed to the upper parts of the two second support plates.

[0055] The specific use process is as follows: in the initial state, the unmanned aerial vehicle 7 and the launch system are both arranged in the box, which is convenient for concealed transportation of the unmanned aerial vehicle 7 and the launch system. When the launch system needs to be mounted, the bottom of the box is first cut open so that the support mechanism is exposed from the bottom of the box, and the support mechanism is installed on the platform of an armored vehicle, a ship or a large aircraft. When the unmanned aerial vehicle 7 needs to be launched, the entire box is cut open and the box is removed. The control system controls the electromagnetic suction component to be energized, and the docking piece 9 on the rotating component 8 of the unmanned aerial vehicle 7 docks with the docking groove on the electromagnetic suction plate 12, and the electromagnetic suction plate 12 adsorbs the docking piece 9. After that, the control system controls the rotating component 8 of the unmanned aerial vehicle 7 to rotate. After reaching the take-off flight threshold by relying on the power of the unmanned aerial vehicle 7 itself, the control system controls the electromagnetic suction component to be powered off, and the electromagnetic suction component no longer adsorbs the docking piece 9. At this time, the unmanned aerial vehicle 7 slides on the launch track to complete the launch.

[0056] The present specification uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core idea of ​​the present invention. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. An unmanned aerial vehicle launch and control device, characterized in that: It includes a box, a launching system and a control system. The launching system is used to be arranged in the box. The launching system includes a supporting mechanism, a launching track and an electromagnetic suction mechanism. The launching track is arranged on the upper part of the supporting mechanism. The launching track is used to place an unmanned aerial vehicle. The electromagnetic suction mechanism is arranged on the upper part of the supporting mechanism. When the electromagnetic suction mechanism is powered on, it can absorb the unmanned aerial vehicle. The electromagnetic suction mechanism and the unmanned aerial vehicle are both connected to the control system signal.

2. The unmanned aerial vehicle launch and control device according to claim 1, characterized in that: When the electromagnetic suction mechanism is powered on, it can absorb the rotating component at the rear end of the unmanned aerial vehicle without affecting the rotation of the rotating component of the unmanned aerial vehicle.

3. The unmanned aerial vehicle launch and control device according to claim 2, characterized in that: The electromagnetic suction mechanism includes a shell, a rotating connection assembly and an electromagnetic suction component. The shell is fixed to the upper part of the support mechanism. The electromagnetic suction component is connected to the shell through the rotating connection assembly. When the electromagnetic suction component is energized, it can absorb the rotating component at the rear end of the unmanned aerial vehicle without affecting the rotation of the rotating component of the unmanned aerial vehicle. The control system is used to control the power on or off of the electromagnetic suction component.

4. The unmanned aerial vehicle launch and control device according to claim 3, characterized in that: It also includes a docking piece, which is used to be fixed on the rotating component at the rear end of the unmanned aerial vehicle. The docking piece can dock with the electromagnetic suction component, so that the axis around which the docking piece and the rotating component of the unmanned aerial vehicle rotate is colinear with the axis around which the electromagnetic suction component rotates, and the circumferential relative movement of the docking piece and the electromagnetic suction component is restricted, and the electromagnetic suction component can adsorb the docking piece when energized.

5. The unmanned aerial vehicle launch and control device according to claim 4, characterized in that: The electromagnetic suction component includes an electromagnetic suction column and an electromagnetic suction plate arranged at one end of the electromagnetic suction column, the rotating connection assembly includes a rolling bearing and a plane bearing, the inner ring of the rolling bearing is fixedly sleeved on the outside of the electromagnetic suction column, the plane bearing is fixedly sleeved on the outside of the outer ring of the rolling bearing, the plane bearing is fixed in the shell, the rolling body of the plane bearing is in contact with one side of the electromagnetic suction plate, and the other side of the electromagnetic suction plate is provided with a docking groove matching the docking piece structure, and the docking piece can be docked with the electromagnetic suction plate through the docking groove.

6. The unmanned aerial vehicle launch and control device according to claim 5, characterized in that: The docking member includes a disc and a positioning block arranged around the disc, the central axis of the disc is colinear with the central axis of the rotating component of the unmanned aerial vehicle, the docking groove includes a circular groove and a positioning groove arranged around the circular groove, the disc is used to extend into the circular groove, and the positioning block is used to extend into the positioning groove.

7. The unmanned aerial vehicle launch and control device according to claim 6, characterized in that: The electromagnetic suction plate is a circular plate, the electromagnetic suction column is a circular column, the central axis of the electromagnetic suction column is collinear with the central axis of the electromagnetic suction plate, and the central axis of the circular groove is collinear with the central axis of the electromagnetic suction plate.

8. The unmanned aerial vehicle launch and control device according to claim 1, characterized in that: The launching track includes two track assemblies, and the two track assemblies are arranged in parallel on the upper part of the supporting mechanism; the track assembly includes a first track, a second track and a locking component, the first track is fixed on the supporting mechanism, the second track is slidably installed on the first track, and the locking component can lock and fix the second track on the first track.

9. The unmanned aerial vehicle launch and control device according to claim 1, characterized in that: The support mechanism includes a first support member, a second support member and an angle adjustment mechanism. The second support member is hinged to the first support member and is located above the first support member. The angle adjustment mechanism is used to adjust the angle between the second support member and the first support member. The launch track and the electromagnetic suction mechanism are both arranged on the upper part of the second support member.

10. The unmanned aerial vehicle launch and control device according to claim 9, characterized in that: The angle adjustment mechanism includes a plurality of angle adjustment components, each of which includes a plurality of angle adjustment blocks, wherein the bottom surface and the top surface of the angle adjustment block are respectively used to fit with the upper portion of the first support member and the lower portion of the second support frame, and the angles between the bottom surface and the top surface of all the angle adjustment blocks in each of the angle adjustment components are the same, and the angle between the bottom surface and the top surface of the angle adjustment block of one angle adjustment component is different from the angle between the bottom surface and the top surface of the angle adjustment block of another angle adjustment component.

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