Multi-rotor unmanned aerial vehicle recycling and putting device

Abstract

The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a multi-rotor unmanned aerial vehicle recycling and putting device. Comprising a cabin, a recovery assembly, a multi-rotor sub-machine, a power supply and a control module, a recovery channel is arranged at the bottom of the cabin; each recovery assembly is composed of a fixing plate, recovery rods and a telescopic push rod, the recovery assemblies are arranged in the cabin in an array mode, and a stopping rope is fixed to the lower ends of every two adjacent recovery rods; a separation assisting plate is arranged between the swinging planes of every two adjacent recovery rods; and an inclined hook is fixed at the top of the multi-rotor sub-aircraft. The recycling assemblies are arranged in an array mode, so that the device can recycle and put a plurality of multi-rotor sub-aircrafts at the same time, and the recycling assemblies are arranged in the cabin, so that the influence on the flight of the mother aircraft is small.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a multi-rotor UAV recovery and deployment device. Background Technology

[0002] Currently, drone reconnaissance technology has been widely applied in military, commercial, and civilian fields. In particular, mother-daughter drones, which carry multiple small multi-rotor drones on a large drone, combine the wide field of view and long range of the large drone with the high flexibility and precise reconnaissance capabilities of a swarm of smaller drones.

[0003] For example, Chinese patent CN116513510A proposes a mother-daughter UAV that carries at least two daughter drones on a mother drone to integrate the advantages of both. However, in this technology, after the daughter drones are released and complete their tasks, they need to land in the work area and cannot return to the mother drone for repeated operations. This results in a weakness in the ability to perform repeated operations due to the inability to recover the drones.

[0004] To address this, Chinese patent CN112158333B proposed an inverted harpoon-shaped mother-daughter UAV release and recovery device. This device utilizes deployable and closable harpoon-shaped narrow wings, along with a wire mesh suspended below the mother UAV, to achieve recovery. However, this recovery and release device is always located outside the mother UAV, significantly impacting its flight performance. Furthermore, the limited range and layout of the wire mesh restricts the number of daughter UAVs that can be simultaneously carried and recovered, affecting the efficiency of daughter UAV operations.

[0005] Therefore, there is currently a lack of a device that has minimal impact on the flight of the mother aircraft and can simultaneously release or recover multiple daughter aircraft. Utility Model Content

[0006] The purpose of this invention is to provide a multi-rotor UAV recovery and deployment device to solve the problem of existing UAV recovery and deployment devices that are difficult to release and recover multiple sub-drones simultaneously and have little impact on the flight of the mother aircraft.

[0007] To achieve the above, this utility model provides the following technical solution:

[0008] A multi-rotor UAV recovery and deployment device includes a cabin that also serves as a wing, a recovery assembly, a multi-rotor sub-unit, a power supply, and a control module. A recovery channel is located at the bottom of the cabin. The recovery assembly is situated directly above the recovery channel and consists of a fixed plate, a recovery rod, and a telescopic push rod. The fixed plate is mounted on the top of the cabin. The upper end of the recovery rod is hinged to the left end of the lower surface of the fixed plate. The fixed end of the telescopic push rod is hinged to the right end of the lower surface of the fixed plate, and the telescopic end of the telescopic push rod is hinged to the middle of the recovery rod. The recovery assemblies are arranged in an array inside the cabin, and an arresting cable is fixedly connected to the lower end of the recovery rods of adjacent recovery assemblies. A release assist plate is provided between the swing planes of adjacent two recovery rods and is fixed to the top of the cabin. A slanted hook is fixed to the top of the multi-rotor sub-unit. The power supply and the control module are both fixed to the bottom of the cabin, and the control module is electrically connected to the power supply and the telescopic push rod.

[0009] Preferably, the inclined hook consists of a buckle and an inclined post fixed to the multirotor sub-engine; the top of the inclined post is provided with an upwardly angled lever, forming a horizontally oriented V-shaped opening; the inclined post and the lever are located on the same side of the central axis of the multirotor sub-engine; a baffle is provided on the side of the top of the inclined post; the buckle is hinged to the top of the inclined post; one end of the buckle is provided with a reverse acute-angle barb, and the other end is provided with a limiting protrusion; a return torsion spring is installed on the side of the inclined post; one torsion arm of the return torsion spring is limited by the baffle; the other torsion arm of the return torsion spring is provided with an L-shaped bend, and the bend rests above the lever and the buckle.

[0010] Preferably, the vertical distance between the release plate and the hinge center of the recovery rod is less than the length of the recovery rod, so that the limiting protrusion of the buckle is in contact with the bottom of the release plate after the recovery rod is lifted.

[0011] Preferably, the telescopic push rod of the recovery assembly extends and retracts synchronously; when the recovery rod is vertical, its lower end extends out from the recovery channel, and the arresting cable remains outside the cabin.

[0012] The beneficial effects of this utility model are as follows:

[0013] (1) The recovery components, arresting cables and release aids, etc., used for the recovery and release of multi-rotor aircraft are all located inside the cabin, which also serves as the wing, so they have little impact on the flight of the mother aircraft.

[0014] (2) The combination of the array-set recovery components, arresting cables and the oblique hooks on the multi-rotor aircraft enables the device to recover multiple multi-rotor aircraft simultaneously.

[0015] (3) The telescopic push rod that extends synchronously, together with the release plate and the buckle, enables the device to simultaneously deploy multiple multi-rotor aircraft inside the cabin. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0017] Figure 2 This is a schematic diagram of the recycling component.

[0018] Figure 3 This is a schematic diagram of the slant hook structure of a multi-rotor aircraft.

[0019] Figure 4 This is a schematic diagram of the recovery of a multi-rotor aircraft.

[0020] Figure 5 This is a schematic diagram of the interior of the multirotor aircraft's cabin.

[0021] Figure 6 This is a schematic diagram of a multi-rotor aircraft being deployed.

[0022] In the diagram, 1. Cabin, 2. Recovery assembly, 201. Fixing plate, 202. Recovery rod, 203. Telescopic push rod, 3. Multirotor sub-engine, 4. Power supply, 5. Control module, 6. Recovery channel, 7. Arresting cable, 8. Release plate, 9. Angled hook, 901. Buckle, 902. Angled column, 903. Lever, 904. Return torsion spring. Detailed Implementation

[0023] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this utility model, and should not be construed as limiting this utility model.

[0024] like Figure 1 , Figure 2As shown, a multi-rotor UAV recovery and deployment device includes a fixed-wing mother aircraft, a cabin 1 that also serves as the wing, a recovery assembly 2, a multi-rotor sub-aircraft 3, a power supply 4, and a control module 5. The fixed-wing mother aircraft is of conventional technology, consisting of wings, a fuselage, and a power system, and will not be described further here. The cabin 1 has a recovery channel 6 at its bottom for the recovery and deployment of the multi-rotor sub-aircraft. The recovery assembly 2 is located directly above the recovery channel 6 and consists of a fixed plate 201, a recovery rod 202, and a telescopic push rod 203. The fixed plate 201 is mounted on the top of the cabin 1. The upper end of the recovery rod 202 is hinged to the left end of the lower surface of the fixed plate 201. The fixed end of the telescopic push rod 203 is hinged to the right end of the lower surface of the fixed plate 201, and the telescopic end of the telescopic push rod 203 is hinged to the middle of the recovery rod 202. The recovery assemblies 2 are arranged in an array inside the cabin 1, and an arresting cable 7 is fixedly connected to the lower end of the recovery rods 202 of adjacent recovery assemblies 2. A release plate 8 is provided between the swing planes of two adjacent recovery booms 202, and the release plate 8 is fixed to the top of the cabin 1. A hook 9 is fixed to the top of the multirotor sub-engine 3; the power supply 4 and the control module 5 are both fixed to the bottom inside the cabin 1, and the control module 5 is electrically connected to the power supply 4 and the telescopic push rod 203. The telescopic push rod 203 of the recovery assembly 2 extends and retracts synchronously. When the multirotor sub-engine 3 needs to be recovered, the telescopic push rod 203 extends, causing the recovery boom 202 to swing clockwise to a vertical position. At this time, the lower end of the recovery boom 202 and the arresting cable 7 on it pass through the recovery channel 6 and remain outside the cabin 1. The multirotor sub-engine 3 can approach from the left side of the cabin 1 and hook the hook 9 onto the arresting cable 7. Subsequently, the telescopic push rod 203 retracts, bringing the multirotor sub-engine 3 back into the cabin 1 through the recovery channel 6.

[0025] like Figure 3 and Figure 4 As shown, the angled hook 9 consists of a buckle 901 and an angled post 902 fixed to the multirotor sub-aircraft 3. The top of the angled post 902 has an upwardly angled lever 903, forming a horizontally oriented V-shaped opening. The angled post 902 and the lever 903 are located on the same side of the center of gravity of the multirotor sub-aircraft 3, specifically... Figure 5The right side of the center. This setting ensures that the lever 903 is always angled upwards under gravity, facilitating subsequent release. A baffle is provided on the side of the top of the inclined column 902. The buckle 901 is hinged to the top of the inclined column 902. One end of the buckle 901 has a reverse acute-angled barb, and the other end has a limiting protrusion. A return torsion spring 904 is installed on the side of the inclined column 902. One torsion arm of the return torsion spring 904 is limited by the baffle, and the other torsion arm of the return torsion spring 904 has an L-shaped bend, which is located above the lever 903 and the buckle 901. When no external force is applied, the upper surface of the buckle 901 coincides with the upper surface of the lever 903, and the barb is located between the V-shaped opening formed by the lever 903 and the inclined column 902, with the acute-angled barb tilted inwards towards the V-shaped opening; the angle between the outer side of the barb and the upper surface of the buckle is 30°. The angle between the inner side of the barb and the lower surface of the latch 901 is 75°. When the multirotor sub-plane 3 approaches the arresting cable 7, the inwardly tilted barb facilitates the arresting cable 7 striking the outer side of the barb and entering the V-shaped opening; when the multirotor sub-plane 3 stops operating, under the action of gravity, the barb can keep the multirotor sub-plane 3 hooked on the arresting cable 7 without falling off. Subsequently, the telescopic push rod 203 shortens, and the recovery assembly 2 recovers the multirotor sub-plane into the cabin 1.

[0026] like Figure 5 and Figure 6 As shown, the vertical distance between the release plate 8 and the hinge center of the recovery rod 202 is less than the length of the recovery rod 202. When the telescopic push rod 203 shortens and the multirotor sub-engine 3 is recovered into the cabin 1, the limiting protrusion of the latch 901 just contacts the bottom of the release plate 8. When the multirotor sub-engine 3 needs to be deployed, the telescopic push rod 203 continues to shorten, the recovery rod 202 drives the arresting cable 7 to rotate counterclockwise, and the bottom of the release plate 8 pushes the limiting protrusion of the latch 901, causing the latch 901 to rotate counterclockwise relative to the lever 903. The barb with an inner angle of 75° prevents the barb from shearing and jamming the arresting cable 7 when the latch 901 rotates. After the barb gradually moves above the lever 903, the arresting cable 7 is no longer obstructed by the barb. Since the lever 903 is angled upward, under the action of gravity, the multi-rotor aircraft 3 cannot be hooked onto the arresting cable 7 by the lever 903 alone. Therefore, the multi-rotor aircraft 3 will fall and leave the cabin 1 from the recovery channel 6, thus realizing the deployment function.

[0027] When it is necessary to recover the multirotor sub-aircraft 3, the telescopic push rod 203 extends again, and the limiting protrusion of the buckle 901 will leave the bottom of the release plate 8. Under the action of the reset torsion spring 904, the barb of the buckle 901 will return to the inside of the V-shaped opening, which facilitates the docking and recovery of the multirotor sub-aircraft 3.

Claims

1. A multi-rotor unmanned aerial vehicle (UAV) recovery and deployment device, characterized in that: It comprises a cabin (1) which is also a wing, a recycling assembly (2), a multi-rotor sub-machine (3), a power supply (4) and a control module (5); the bottom of the cabin (1) is provided with a recycling channel (6); The recycling assembly (2) is located directly above the recycling channel (6), and the recycling assembly (2) is composed of a fixed plate (201), a recycling rod (202) and a telescopic push rod (203); the fixed plate (201) is installed on the top of the cabin (1); the upper end of the recycling rod (202) is hinged to the lower surface of the left end of the fixed plate (201); the fixed end of the telescopic push rod (203) is hinged to the lower surface of the right end of the fixed plate (201); the telescopic end of the telescopic push rod (203) is hinged to the middle of the recycling rod (202); the recycling assembly (2) is arranged in an array inside the cabin (1), and the lower ends of the recycling rods (202) of adjacent two recycling assemblies (2) are fixedly connected with a blocking cable (7); a detaching aid plate (8) is arranged between the swing planes of adjacent two recycling rods (202), and the detaching aid plate (8) is fixed to the top of the cabin (1); The top of the multi-rotor sub-machine (3) is fixed with an inclined hook (9); the power supply (4) and the control module (5) are both fixed to the bottom inside the cabin (1), and the control module (5) is electrically connected with the power supply (4) and the telescopic push rod (203).

2. The multi-copter unmanned aerial vehicle recovery and launch apparatus of claim 1, wherein: The inclined hook (9) is composed of a buckle (901) and an inclined column (902) fixed to the multi-rotor sub-machine (3); the top of the inclined column (902) is provided with an upward inclined push rod (903), forming a horizontally oriented V-shaped opening; the inclined column (902) and the push rod (903) are located on the same side of the central axis plane of the multi-rotor sub-machine (3); the side surface of the top of the inclined column (902) is provided with a baffle; the buckle (901) is hinged to the top of the inclined column (902); one end of the buckle (901) is provided with a reverse acute angle barb, and the other end is provided with a limiting protrusion; a reset torsional spring (904) is installed on the side surface of the inclined column (902); one torsional arm of the reset torsional spring (904) is limited by the baffle; the other torsional arm of the reset torsional spring (904) is provided with an L-shaped corner, and the corner leans on the push rod (903) and the buckle (901).

3. The multi-copter unmanned aerial vehicle recovery and launch apparatus of claim 2, wherein: The vertical distance between the hinge center of the detaching aid plate (8) and the recycling rod (202) is less than the length of the recycling rod (202), so that the limiting protrusion of the buckle (901) is in contact with the bottom of the detaching aid plate (8) when the recycling rod (202) is lifted.

4. The multi-copter unmanned aerial vehicle recovery and launch apparatus of claim 1, wherein: The telescopic push rod (203) of the recycling assembly (2) is synchronous telescopic; when the recycling rod (202) is vertical, the lower end extends out of the recycling channel (6), and the blocking cable (7) is kept outside the cabin (1).

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